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F-16 Fighting Falcon 

Overview

Variants F-16A F-16C and F-16D Service Life Specifications
Images
F-16 Images
Block 50D/52D F-16CJ Wild Weasel Related FAS Blog Posts
Sources and Resources
Foreign Military Sales

 

Genesis of the successful F-16 fighter/attack aircraft lies in reaction to severe deficiencies in US fighter design revealed by the Vietnam War.

Following the success of the small, highly maneuverable F-86 day fighter in the Korean War, US fighter design changed to emphasize maximum speed, altitude, and radar capability at the expense of maneuverability, pilot vision, and other attributes needed for close combat. This trend reached its extremity in the McDonnell Douglas F-4 Phantom, which was the principal fighter for both the US Air Force and Navy during the latter part of the Vietnam War.

The F-4 was originally designed as an interceptor for defense of the fleet against air attack - a mission neither it nor any other jet has ever executed, because no US fleet has come under air attack since the beginning of the jet age. Be that as it may, the F-4 interceptor was designed to meet the fleet defense mission by using rapid climb to high altitude, high supersonic speed, and radar-guided missiles to shoot down threat aircraft at long distance.

Used as a fighter rather than as an interceptor in Vietnam, the F-4 was severely miscast. Against very inferior North Vietnamese pilots flying small, highly maneuverable MiG-21s, the air-to-air kill ratio sometimes dropped as low as 2 to 1, where it had been 13 to 1 in Korea. As the Vietnam War drew to a close, it was generally agreed that the F-4 had prohibitive deficiencies including:

  1. LARGENESS. F-4 pilots to frequently found themselves fighting at separation distances at which they could not see the smaller MiG-21s, but the MiG-21 pilots could see them.
  2. POOR PILOT VISION. In order to minimize high-speed drag, the F-4, and all combat aircraft before the F-14, does not have a bubble canopy. It is designed for a pilot to look straight ahead. Vision down and to the sides is poor; vision to the rear is nonexistent.
  3. MANEUVERABILITY. While the F-4 can pull 7G in turns, which was acceptable for that time, it can only do so by rapidly bleeding off energy (losing speed and/or altitude).
  4. TRANSIENT PERFORMANCE. Ability of the F-4 to change its maneuver (that is, to roll rapidly while pulling high Gs) was poor.
  5. COST. The large F-4 was an expensive aircraft to procure and maintain. This meant that, compared to the MiG-21, fewer aircraft could be bought with a given budget.
  6. NO GUN. The F-4 was designed without a gun, and was thus not capable of very close combat.
  7. COMBAT PERSISTENCE. While the ferry range of the F-4 was acceptable, its ability to engage in sustained hard maneuvering without running out of fuel was a significant problem.
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These various sacrifices were rationalized by the belief that visual dogfighting was obsolete, and that in the supersonic age, air combat would be fought beyond visual range (BVR) using radar-guided missiles. This concept failed in Vietnam for two reasons: First, radar could detect and track aircraft but not identify them. Operating beyond visual range created an unacceptable risk of shooting down one's own aircraft. Pilots were therefore required to close to visually identify the target before shooting; this eliminated the theoretical range advantage of radar-guided missiles. Second, the performance of the Sparrow radar-guided missile in Vietnam was poor, generally yielding less than 10% kill per shot.

Dissatisfaction with these deficiencies led to the US Air Force F-15 and US Navy F-14 designs. On this page we discuss only the Air Force programs.

The original F-15 had excellent pilot vision, including being able to see 360 degrees in the horizontal plane. It had strong high-speed maneuverability and a 20mm cannon. In addition to rectifying some of the F-4's deficiencies, it could fly higher and faster than the F-4, and had dramatically better climb and acceleration.

It also had a powerful radar with advanced look-down shoot-down capability, and relied on the Sparrow missile as its principal weapon.

Nevertheless, an informal but influential group called the "Fighter Mafia" objected to the F-15 as moving in the wrong direction. (The most prominent Fighter Mafia spokesmen were systems analyst Pierre Sprey, test pilot Charles E. Meyers, and legendary fighter pilot John Boyd.)

The F-15, the Fighter Mafia objected, was even larger and more expensive than the F-4. Much of that money went into creating high maximum speed (Mach 2.5) and altitude (65,000 feet) and to serving as a launcher, under BVR conditions which couldn't be used in real combat,. for the Sparrow missile which didn't work While recognizing that the F-15 had phenomenal supersonic climb and maneuverability (it could sustain 6Gs at Mach 1.6), at such speeds it could not fight because its turn radius was so large that it could not keep the enemy in sight.Return to Top

What the Air Force needed, the Mafia argued, was a successor to the WWII P-51 Mustang and the Korean War F-86 Saber: an all-new small fighter that would be cheap enough to buy in large numbers. (The F-104 was not considered a predecessor aircraft because, while it had excellent climb and acceleration, its wings were too small, leaving it deficient in range and maneuverability.) The new fighter would have revolutionary maneuverability, transient performance, acceleration, and climb at the subsonic and transonic speeds at which air combat is actually fought. It would have a gun and its primary armament would be the infra-red guided Sidewinder missile that had proven highly effective in Vietnam.

While Sidewinder's range was limited to about three miles, the Mafia argued that air combat beyond that range was fantasy in any case. Some members of the Mafia even suggested that the ideal small fighter would have no radar at all, although this was a minority view.

In any case, the Air Force establishment wanted no part of a new small fighter, with or without radar. It was regarded as a threat to the F-15, which was USAF's highest priority program. But the Fighter Mafia gained considerable resonance in Congress and within the Office of the Secretary of Defense. In 1971 Deputy Secretary of Defense David Packard began a Lightweight Fighter (LWF) program to explore the concept.

The LWF was to be about 20,000 pounds, or half the weight of the F-15, and was to stress low cost, small size, and very high performance at speed below Mach 1.6 and altitude below 40,000 feet. Two competing designs would be chosen for prototyping.

Industry recognized, correctly, that regardless of USAF hostility, LWF variants had great potential for profitable foreign military sales, including replacing the F-104. Single-engine designs were put forward by Boeing, General Dynamics, LTV, Northrop, and Rockwell. Northrop also proposed on a twin-engine design, in effect using Air Force money to develop a replacement for its F-5 export fighter.  Return to Top

The Boeing and General Dynamics designs were the clear leaders from the beginning, with the Northrop twin-engine design clearly the weakest of the six.

But midway through this stage of the competition, some potential foreign buyers expressed concern over buying a new single-engine fighter. The previous single-engine supersonic export fighter, the F-104, had a troublesome safety record that some buyers were disinclined to repeat.

USAF, therefore, decided that one of the two down-selectees had to have two engines. Since the last-place Northrop design was the only twin-engine contender, it became a down-selection winner by default.

When the General Dynamics design was chosen the other selectee on merit, Boeing was no doubt a bit miffed that its loss was caused by USAF changing the rules in mid-competition. But it did not protest the decision.

Of the two surviving designs, now designated the General Dynamics YF-16 and the Northrop YF-17., the YF-17 was a relatively conventional design, to some extent an outgrowth of the F-5, while the YF-16 was an all-new design incorporating highly innovative technologies that in many respects reached beyond those of the more expensive F-15. These included -     Return to Top

  1. FLY BY WIRE. From the outset, the YF-16 had no direct connection between the pilot's controls and the aircraft's control surfaces. Instead, the stick and rudder controls were connected to quadruple-redundant computers, which then told the elevators, ailerons, and rudder what to do. This had several large advantages over previous systems. It was quicker responding, automatically correcting for gusts and thermals with no effort from the pilot. It could be programmed to compensate for aerodynamic problems and fly like an ideal airplane. Most importantly, it enabled, with full safety, a highly efficient unstable design.
  2. NEGATIVE STABILITY. All previous aircraft designs had been aerodynamically stable. That is, the center of gravity was well in front of the center of lift and the center of pressure (drag).
    1. To illustrate the difference between stable and unstable designs, take a shirt cardboard and, holding it by the leading edge, pull it rapidly through the air. It will stretch out behind your hand in a stable manner. This is a stable design Now take it by the trailing edge push forward from there. It will immediately flip up or down uncontrollably. That is an unstable design.
    2. The downside of aerodynamic stability is that the aircraft is nose-heavy and always trying to nose down. The elevator must therefore push the tail down to level the airplane. But in addition to rotating the airplane from nose-down to level, the elevator is exerting negative lift; that is, it is pushing the airplane down. In order to counteract this negative lift, the wing needs to be made larger to create more positive lift. This increases both weight and drag, decreasing aircraft performance. In pitch-up situations including hard turns which are the bread and butter of aerial combat, this negative effect is greatly magnified.
    3. The YF-16 became the world's first aircraft to be aerodynamically unstable by design. With its rearward center of gravity, its natural tendency is to nose up rather than down. So level flight is created by the elevator pushing the tail up rather than down, and therefore pushing the entire aircraft up. With the elevator working with the wing rather than against it, wing area, weight, and drag are reduced. The airplane was constantly on the verge of flipping up or down totally out of control,. and this tendency was being constantly caught and corrected by the fly-by-wire control system so quickly that neither the pilot nor an outside observer could know anything was happening. If the control system were to fail, the aircraft would instantly disintegrate; however, this has never happened.
  3. HIGH G LOADS. Previous fighters were designed to take 7Gs, mainly because it was believed that the human pilot, even with a G-suit, could not handle more. The YF-16 seatback was reclined 30 degrees, rather than the usual 13 degrees. This was to increase the ability of the pilot to achieve 9Gs by reducing the vertical distance between head and heart. Additionally, the traditional center control stick was replaced by a stick on the right side, with an armrest to relieve the pilot of the need to support his arm when it weighed nine times normal.
  4. PILOT VISION. In addition to allowing full-circle horizontal vision and unprecedented vision over the sides, the YF-16 canopy was designed without bows in the forward hemisphere.
  5. GROWTH PREVENTION. Traditionally, room for growth has been considered an asset. Fighter aircraft have averaged weight gain of about one pound per day as new capabilities are added, cost increases, and performance declines. The F-15, for example, was designed with about 15 cubic feet of empty space to allow for future installation of additional equipment.. In a radical departure, the YF-16 was intentionally designed with very little empty space, (about two cubic feet)., with the explicit intention of preventing growth. One member of the House Armed Services Committee actually wrote to the Secretary of the Air Force asking that the F-16's empty space be filled with Styrofoam to insure that "gold-plated junk" was not added to the design.
  6. COMBAT RADIUS AND PERSISTENCE. General Dynamics chose a single turbofan engine, essentially the same engine as one of the two that powered the F-15. Use of a single engine helped minimize weight and drag; use of a turbofan rather than a pure jet engine gave high fuel efficiency. Additionally, the YF-16 designers used a "blended body" design in which the wing gradually thickened at the root and blended into the body contours without the usual visible joint. The space thus created was filled with fuel. With such a high fuel fraction and a fuel-efficient engine, the YF-16 was able to break the presumption that small aircraft were necessarily short-ranged.
  7. RADAR INTEGRATION. Because the YF-16 carried no radar-guided missiles, it could only fight within visual range. Moreover, the small weight and space available limited the range of its radar. Nevertheless, it was given a technologically advanced small radar, with excellent look-down capability. Most importantly, the radar was integrated with the visual combat mode. That is, the radar projected an image of the target aircraft onto the Head Up Display so that, by looking at that image, the pilot was looking exactly where the target would become visible as he approached it.  Return to Top

The competing Northrop YF-17 design was somewhat larger than the YF-16, and used two smaller pure jet engines. At the price of reduced range and persistence, the YF-17 avoided the main problem of the YF-16's turbofan: the inertia of the large fan required too long - in some cases six seconds - to spool up from idle to full power. In other respects, the YF-17 progressed better than expected, given its initial last place position.

Northrop argued that its twin-engine design added an essential safety factor, citing its experience with the small twin-engine F-5 fighter as an example. USAF did not find this persuasive, in part because a two engine plane with one engine out is useless in combat, and the probability of an engine failure was nominally twice as high with two engines as with one. The higher performance, better transient maneuverability, longer range, and lower cost of the YF-16 carried the day, and in 1976 the F-16 was chosen over the F-17.

USAF was then in the uncomfortable position of having a lightweight fighter design that could outmaneuver and outrange its pride and joy, the F-15 air superiority fighter. In real-world combat conditions, which meant Mach 1.2 or below, the F-16s held a significant edge over the F-15. To some extent this problem was solved by designating the F-16 as a "swing fighter" to do both air-to-air and air-to-ground, while the F-15 was to continue its aristocratic mission of pure air-to-air.

Probably the F-16's greatest asset during development was its unpopularity with the USAF establishment. Knowing that their airplane was in constant threat of cancellation, the General Dynamics designers were inspired to do everything possible and then some to maintain performance and prevent cost growth. For example, while the F-15 was about 25% titanium, titanium in the F-16 was limited to 2%. As another example, a fixed engine inlet was used to hold down cost, even though a variable inlet would have given better performance above Mach 1.5. Return to Top

The F-16 has been, by any standard, a success. USAF has used it heavily and successfully for air-to-ground in the 1991 Gulf war and all subsequent conflicts. The Israeli Air Force has also had great success with it.

With the benefit of hindsight, it is worthwhile to look back from the current (2003) vantage point to see how the original concept has faired.

  1. FLY BY WIRE has been a clear success. It is now used in essentially all military fixed wing aircraft and on many commercial aircraft.
  2. NEGATIVE STABILITY, or at least reduced positive stability, has worked without a failure - no F-16s have disintegrated in air from control system failure - and is coming into increasing use.
  3. HIGH G LOADS. The 9G standard pioneered by the F-16 is now universal for new fighter designs, although it is achieved more by pilot training than by hardware. Benefit of the 30-degree reclining seat back has not been clearly established, and many pilots find it increases the difficult of checking their six o'clock position while in hard maneuvers. So more recent designs have not copied the F-16 seat. Similarly, the side stick has worked well but has not proven as essential as its designers originally expected. One enduring controversy is whether control systems should, as is the case with the F-16 be programmed to unconditionally limit the aircraft to 9gs, or whether higher loads should be permitted in emergencies. One eminent General Dynamics test pilot, a "super pilot" who in his fifties was still able to sustain 9Gs for 45 seconds, published an article on the subject in "Code One", the General Dynamics house organ, arguing that there was not enough useful benefit in being able to exceed 9 Gs to justify the strain on the airframe, particularly since few pilots could retain functionality above 9Gs. Tragically and ironically, this pilot was killed when his plane, pulling 9Gs in a hard maneuver, was unable to pull up enough to avoid the impacting the ground. This outstanding pilot might have been able to function with a brief application of 10, 11, or even 12Gs. Could that have saved him and his aircraft? Could it save others in the future?
  4. PILOT VISION. Pilots like the F-16 canopy without front bows for its quietness as well as its vision. One drawback is that in order to avoid optical distortion in the bowless design, the conventional use of thick polycarbonate on the front to protect against birdstrike, and thinner polycarbonate for the rest of the canopy, cannot be used. Because the F-16 canopy uses thick polycarbonate throughout, it is not possible to eject by using the seat to puncture through the canopy. The canopy must first be blown off by small rockets, prolonging the ejection sequence slightly. On balance, the F-16 canopy concept is considered successful and it is continued in the F-22. On the other hand, neither Joint Strike Fighter candidate used full-circle vision, much less a bowless canopy.
  5. GROWTH PREVENTION. The original concept of a small day ait-to-air fighter was lost before the first production aircraft. The fuselage was extended so that the single-seat versions became as long as the two-seat version, and air-to-ground capability was added. As its life progressed, the F-16 became progressively larger and heavier as more capability, including the AMRAAM radar-guided missile, chaff and flare dispensers, and more hard points were added. Still, weight gain has been only about half the traditional pound per day, so the determination of the original designers has not been in vain.
  6. COMBAT RADIUS AND PERSISTENCE. The F-16 blended body has worked well, but has not been emulated in most newer designs.
  7. RADAR INTEGRATION. Integration of radar with visual systems has been fully successful and is now standard fighter design.  Return to Top

Variants  Return to Top

In January 1972, the Lightweight Fighter Program solicited design specifications from several American manufacturers. Participants were told to tailor their specifications toward the goal of developing a true air superiority lightweight fighter. General Dynamics and Northrop were asked to build prototypes, which could be evaluated with no promise of a follow-on production contract. These were to be strictly technology demonstrators. The two contractors were given creative freedom to build their own vision of a lightweight air superiority fighter, with only a limited number of specified performance goals. Northrop produced the twin-engine YF-17, using breakthrough aerodynamic technologies and two high-thrust engines. General Dynamics countered with the compact YF-16, built around a single F100 engine.

When the Lightweight Fighter competition was completed early in 1975, both the YF-16 and the YF-17 showed great promise. The two prototypes performed so well, in fact, that both were selected for military service. On 13 January 1975 the Air Force announced that the YF-16's performance had made it the winner of its Air Combat Fighter (ACF) competition. This marked a shift from the original intention to use the two airplanes strictly as technology demonstrators. General Dynamics' YF-16 had generally shown superior performance over its rival from Northrop. At the same time, the shark-like fighter was judged to have production costs lower than expected, both for initial procurement and over the life cycle of the plane. At the same time, the YF-16 had proved the usefulness not only of fly-by-wire flight controls, but also such innovations as reclined seat backs and transparent head-up display (HUD) panels to facilitate high-G maneuvering, and the use of high profile, one-piece canopies to give pilots greater visibility. Thus, the Air Force had its lightweight fighter, the F-16.

The original F-16 was designed as a lightweight air-to-air day fighter. Air-to-ground responsibilities transformed the first production F-16s into multirole fighters. The empty weight of the Block 10 F-16A is 15,600 pounds. The empty weight of the Block 50 is 19,200 pounds. The A in F-16A refers to a Block 1 through 20 single-seat aircraft. The B in F-16B refers to the two-seat version. The letters C and D were substituted for A and B, respectively, beginning with Block 25. Block is an important term in tracing the F-16's evolution. Basically, a block is a numerical milestone. The block number increases whenever a new production configuration for the F-16 is established. Not all F-16s within a given block are the same. They fall into a number of block subsets called miniblocks. These sub-block sets are denoted by capital letters following the block number (Block 15S, for example). From Block 30/32 on, a major block designation ending in 0 signifies a General Electric engine; one ending in 2 signifies a Pratt & Whitney engine.

The F-16A, a single-seat model, first flew in December 1976. The first operational F-16A was delivered in January 1979 to the 388th Tactical Fighter Wing at Hill Air Force Base, Utah. The F-16B, a two-seat model, has tandem cockpits that are about the same size as the one in the A model. Its bubble canopy extends to cover the second cockpit. To make room for the second cockpit, the forward fuselage fuel tank and avionics growth space were reduced. During training, the forward cockpit is used by a student pilot with an instructor pilot in the rear cockpit.   Return to Top

  • Block 1 and Block 5 F-16s were manufactured through 1981 for USAF and for four European air forces. Most Blocks 1 and 5 aircraft were upgraded to a Block 10 standard in a program called Pacer Loft in 1982.
  • Block 10 aircraft (312 total) were built through 1980. The differences between these early F-16 versions are relatively minor.
  • Block 15 aircraft represent the most numerous version of the more than 3,600 F-16s manufactured to date. The transition from Block 10 to Block 15 resulted in two hardpoints added to the chin of the inlet. The larger horizontal tails, which grew in area by about thirty percent are the most noticeable difference between Block 15 and previous F-16 versions.

The F-16C and F-16D aircraft, which are the single- and two-place counterparts to the F-16A/B, incorporate the latest cockpit control and display technology. All F-16s delivered since November 1981 have built-in structural and wiring provisions and systems architecture that permit expansion of the multirole flexibility to perform precision strike, night attack and beyond-visual-range interception missions. All active units and many Air National Guard and Air Force Reserve units have converted to the F-16C/D, which is deployed in a number of Block variants. Return to Top

  • Block 25 added the ability to carry AMRAAM to the F-16 as well as night/precision ground-attack capabilities, as well as an improved radar, the Westinghouse (now Northrop-Grumman) AN/APG-68, with increased range, better resolution, and more operating modes.
  • Block 30/32 added two new engines -- Block 30 designates a General Electric F110-GE-100 engine, and Block 32 designates a Pratt & Whitney F100-PW-220 engine. Block 30/32 can carry the AGM-45 Shrike and the AGM-88A HARM, and like the Block 25, it can carry the AGM-65 Maverick.
  • Block 40/42 - F-16CG/DG - gained capabilities for navigation and precision attack in all weather conditions and at night with the LANTIRN pods and more extensive air-to-ground loads, including the GBU-10, GBU-12, GBU-24 Paveway laser-guided bombs and the GBU-15. Block 40/42 production began in 1988 and ran through 1995. Currently, the Block 40s are being upgraded with several Block 50 systems: ALR-56M threat warning system, the ALE-47 advanced chaff/flare dispenser, an improved performance battery, and Falcon UP structural upgrade.
  • Block 50/52 Equipped with a Northrop Grumman APG-68(V)7 radar and a General Electric F110-GE-129 Increased Performance Engine, the aircraft are also capable of using the Lockheed Martin low-altitude navigation and targeting for night (LANTIRN) system. Technology enhancements include color multifunctional displays and programmable display generator, a new Modular Mission Computer, a Digital Terrain System, a new color video camera and color triple-deck video recorder to record the pilot's head-up display view, and an upgraded data transfer unit. In May 2000, the Air Force certitified Block 50/52 [aka Block 50 Plus] F-16s to carry the CBU-103/104/105 Wind-Corrected Munitions Dispenser, the AGM-154 Joint Stand-Off Weapon, the GBU-31/32 Joint Direct Attack Munition, and the Theater Airborne Reconnaissance System. Beginning in mid-2000, Lockheed-Martin began to deliver Block 50/52 variants equipped with an on-board oxygen generation system (OBOGS) designed to replace the obsolete, original LOX system.
  • Block 50D/52D Wild Weasel F-16CJ (CJ means block 50) comes in C-Model (1 seat) and D-Model (2 seat) versions. It is best recognized for its ability to carry the AGM-88 HARM and the AN/ASQ-213 HARM Targeting System (HTS) in the suppression of enemy air defenses [SEAD] mission. The HTS allows HARM to be employed in the range-known mode providing longer range shots with greater target specificity. This specialized version of the F-16, which can also carry the ALQ-119 Electronic Jamming Pod for self protection, became the sole provider for Air Force SEAD missions when the F-4G Wild Weasel was retired from the Air Force inventory. The lethal SEAD mission now rests solely on the shoulders of the F-16 Harm Targeting System. Although F-18s and EA-6Bs are HARM capable, the F-16 provides the ability to use the HARM in its most effective mode. The original concept called for teaming the F-15 Precision Direction Finding (PDF) and the F-16 HTS. Because this teaming concept is no longer feasible, the current approach calls for the improvement of the HTS capability. The improvement will come from the Joint Emitter Targeting System (JETS), which facilitates the use of HARM's most effective mode when launched from any JETS capable aircraft.
  • Block 60 - In May 1998 the UAE announced selection of the Block 60 F-16 to be delivered between 2002-2004. The upgrade package consists of a range of modern systems including conformal fuel tanks for greater range, new cockpit displays, an internal sensor suite, a new mission computer and other advanced features including a new agile beam radar.

The Common Configuration Implementation Program (CCIP) for the USAF's F-16C/D fleet provides significant avionics upgrades to Block 40 and 50 F-16s, ensuring their state-of-the-art capability well into the 21st century. A key element of the upgrade is a common hardware and software avionics configuration for these two blocks that will bring together the Block 40/42 and 50/52 versions into a common configuration of core avionics and software. The avionics changes consist of the following systems: Link 16 Multifunctional Information Distribution System (MIDS), Joint Helmet-Mounted Cueing System (JHMCS), commercial expanded programmable display generator, color multifunction display set, modular mission computer, mux loadable data entry display set and an electronic horizontal situation display. This package contains a number of systems being incorporated into European F-16s in the F-16A/B Mid-Life Update program. The first aircraft upgraded under CCIP were delivered to combat units in December 2001 (1 ). The Air Force will soon be flying only Block 40/42 and Block 50/52 F-16s in its active-duty units. Block 25 and Block 30/32 will be concentrated in Air National Guard and Air Force Reserve units.

Service Life    Return to Top

The Falcon Up Structural Improvement Program program incorporates several major structural modifications into one overall program, affecting all USAF F-16s. Falcon Up will allow Block 25/30/32 aircraft to meet a 6000 hour service life, and allow Block 40/42 aircraft to meet an 8000 hour service life.

In view of the challenges inherent in operating F-16s to 8,000 flight hours, together with the moderate risk involved in JSF integration, the Department has established a program to earmark by FY 2000 some 200 older, Block 15 F-16 fighter aircraft in inactive storage for potential reactivation. The purpose of this program is to provide a basis for constituting two combat wings more quickly than would be possible through new production. This force could offset aircraft withdrawn for unanticipated structural repairs or compensate for delays in the JSF program. Reactivating older F-16s is not a preferred course of action, but represents a relatively low-cost hedge against such occurrences.

Specifications  Return to Top

Primary Function Multirole fighter
Builder Lockheed Martin Corp.
Power Plant F-16C/D:
one Pratt and Whitney F100-PW-200/220/229 or
one General Electric F110-GE-100/129
Thrust F-16C/D, 27,000 pounds(12,150 kilograms)
Length 49 feet, 5 inches (14.8 meters)
Height 16 feet (4.8 meters)
Wingspan 32 feet, 8 inches (9.8 meters)
Speed 1,500 mph (Mach 2 at altitude)
Ceiling Above 50,000 feet (15 kilometers)
Maximum Takeoff Weight 37,500 pounds (16,875 kilograms)
Combat Radius [F-16C]
  • 740 nm (1,370 km) w/
    2 2,000-lb bombs + 2 AIM-9 + 1,040 US gal external tanks
  • 340 nm (630 km) w/
    4 2,000-lb bombs + 2 AIM-9 + 340 US gal external tanks
  • 200 nm (370 km) + 2 hr 10 min patrol
    w/ 2 AIM-7 + 2 AIM-9 + 1,040 US gal external tanks
Range Over 2,100 nm (2,425 mi; 3,900 km)
Armament One M-61A1 20mm multibarrel cannon with 500 rounds; external stations can carry up to six air-to-air missiles, conventional air-to-air and air-to-surface munitions and electronic countermeasure pods.
MK MK AGM AGM CBU CBU CBU GBU GBU AIM AIM 20
82 84 65 88 87 89 97 10 12 9 120 MM
6







2 2 500

2






2 2 500


2





2 2 500



2




2 2 500




4



2 2 500





4


2 2 500






4

2 2 500







2
2 2 500








6 2 2 500









2 4 500










6 500
Systems
Unit cost $FY98
[Total Program]
F-16C/D, $26.9 million [final order]
Crew F-16C: one; F-16D: one or two
Date Deployed January 1979
Total Production
[for USAF]

1-seat
F-16 A&C
2-seat
F-16 B&D
TOTAL
Block 1 21 22 43
Block 5 89 27 116
Block 10 145 25 170
Block 15 409 46 455
Block 25 209 35 244
Block 30 360 48 408
Block 32 56 5 61
Block 40 234 31 265
Block 42 150 47 197
Block 50 175 28 203
Block 52 42 12 54
F-16A/B 674 121 795
F-16C/D 1,216 205 1,421
TOTAL 1,890 326 2,216
F-16C Block 50 currently in production
Final 3 aircraft ordered in FY1998
15 aircraft to be delivered after 01 Jan 99
Final aircraft of 2216 delivered March 2001
Inventory
As of Sept. 30, 2001

PAI TAI
Active Duty 638 735
Air National Guard 462 576
Air Force Reserve 59 70
Totals 1159 1381
PMAI
Primary Mission Aircraft Inventory
246 Air Combat Command
126 Pacific Air Forces
72 US Air Forces Europe
60 Air Force Reserve
315 Air National Guard
105 Air National Guard Air Defense Force
924 TOTAL Only combat-coded aircraft
Excludes development/ test, attrition reserve, depot maintenance, and training aircraft.

F-16 Mission Missile Configurations

F-16 Rail Stores Loadings
Right Wing           Center           Left Wing
Rail ID   9 8 7 7a 6 5R 5 5L 4 3a 3 2 1
Defensive Counterair   AMRAAM AMRAAM Sidewinder   370g Tank       370g Tank   Sidewinder AMRAAM AMRAAM
Interdiction 1   AMRAAM
GBU24   370g Tank   LANTIRN   370g Tank   GBU24
AMRAAM
Interdiction 2   Sidewinder
AGM65   370g Tank   ECM Pod   370g Tank   AGM65
Sidewinder
Suppress Enemy Air Defense   Sidewinder   Harm   370g Tank   LANTIRN   370g Tank   Harm   Sidewinder

Images   Return to Top

VRML 3-D Model

F-16 Fighting Falcon
VRML by Soji Yamakawa

F-16 Fighting Falcon
Thunderbirds
VRML by Soji Yamakawa


F-16 Images Return to Top

Block 50D/52D F-16CJ Wild Weasel Return to Top

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  • F-16 COMBAT AIRCRAFT FUNDAMENTALS MULTI-COMMAND HANDBOOK 11-F16 VOLUME 5 : 10 MAY 1996 [4478kb PDF, and well worth the wait for the serious trivia buff] This handbook provides F-16 pilots a single-source, comprehensive document containing fundamental employment procedures and techniques that may be used to accomplish the various missions of the F-16. This handbook is the primary F-16 fighter fundamentals reference document for Air Combat Command (ACC), Pacific Air Forces (PACAF), United States Air Forces in Europe (USAFE), Air Force Reserve (USAFR), Air National Guard (ANG), and Air Education and Training Command (AETC). Designed to be used in conjunction with MCM 3–1 (S) and AFI/MCI 11-series directives, this handbook addresses basic flying tasks and planning considerations for both the air-to-air and air-to-surface arenas. It presents a solid foundation on which effective tactics can be developed. This handbook is not designed to be used as a step-by-step checklist of how to successfully employ fighters, but rather provides information and guidelines on basic procedures and techniques.
  • PILOT OPERATIONAL PROCEDURES--F-16 MULTI-COMMAND INSTRUCTION 11-F16 VOLUME 3 21 APRIL 1995 -- [185kb PDF] This instruction prescribes standard operational and weapons employment procedures to be used by all tactical pilots operating USAF F-16 aircraft.
  • General Dynamics F-16 by Joe Baugher
  • General Dynamics F-16 "Fighting Falcon" @ National Museum of the USAF Fact Sheets
  • STP - F-16 MLU Most extensive article on the F-16 Mid-Life Update available anywhere
  • F-16 Evolution (article from July 1997 Code One Magazine)
  • F-16 Fighting Falcon - Lockheed Martin Corp.
  • ANNEX F Common Solution/Concept List (U) Air Force Mission Area Plan (MAP) [as of 11 July 1997 - Rev 10] - Detailed and comprehensive Air Combat Command descriptions of weapon system modernization efforts required to satisfy known needs.
  • 1Lockheed Martin – USAF Teamwork Moves F-16 CCIP Modification Ahead of Schedule

Foreign Military Sales    Return to Top

Taiwan

  • TAIWAN'S AIR FORCE TO ESTABLISH 'ELECTRONIC WAR' UNIT (CNA-Taiwan) 22 December 1999 -- The United States is scheduled to deliver air-launched harpoon missiles to Taiwan next month, and the missiles, to be installed on Taiwan's F-16 fighters, will largely enhance the fighters' long-distance strike capability.
  • DEFENSE MINISTER OUTLINES AIR FORCE PROBLEMS (CNA-Taiwan) 20 December 1999 -- Since March 1998, four of Taiwan's US-made F-16 jet fighters and two French-made Mirage 2000-5 jet fighters have crashed during training flights, causing widespread concern over the air force's flight safety control measures.
  • ANOTHER F-16 SQUADRON COMMISSIONED (CNA-Taiwan) 16 December 1999 -- Taiwan on Thursday inaugurated another F-16 squadron at an air base in Hualien, eastern Taiwan. The next squadron of the US-made fighters is scheduled to be commissioned early next year, also in Hualien.
  • US TENTATIVELY AGREES TO SELL AIM-120 MISSILES TO ROC Central News Agency [Taiwan] 07 December 1999 -- The United States has tentatively agreed to sell AIM-120 advanced medium-range air-to-air missiles to the Republic of China, the Air Force General Headquarters (AFGH) announced on Tuesday.
  • ROC AIR FORCE POSTPONES INTRODUCTION OF F-16'S INTO ACTIVE SERVICE China News [Taiwan] 18 August 1999 -- Prompted by another crash of a US-made F-16 jet fighter on Wednesday, the Republic of China Air Force announced the postponement of plans to introduce the fighters into active service.
  • US ANNOUNCES SALE OF FIGHTER, TRANSPORT AIRCRAFT PARTS TO TAIWAN Central News Agency [Taiwan] 31 July 1999 -- The US Department of Defense announced on Friday the possible sale to Taiwan of spare parts for its F-5E/F, IDF, F-16A/B fighters and C-130H transport aircraft, for an estimated US$150 million.
  • F-16 FIGHTERS RESUME SERVICE Central News Agency [Taiwan] 21 July 1999 -- The Republic of China's Air Force General Headquarters (AFGH) announced on Wednesday that all of its F-16 jet fighters have completed comprehensive security checks and resumed training flights.

United Arab Emirates

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