Tag Archives: Fighter

1 February 1975

Streak Eagle over St. Louis
Major Roger J. Smith, U.S. Air Force

1 February 1975: Major Roger J. Smith, United States Air Force, a test pilot assigned to the F-15 Joint Test Force at Edwards AFB, California, flew the  McDonnell Douglas F-15A-6-MC 72-0119, Streak Eagle, to its eighth Fédération Aéronautique Internationale (FAI) and U.S. National Aeronautic Association time-to-altitude record.

From brake release at Grand Forks Air Force Base, North Dakota, at 913 feet (278 meters) above Sea Level, the F-15 reached 30,000 meters (98,425 feet) in 3 minutes, 27.799 seconds.

This was the eighth time-to-altitude record set by Streak Eagle in 17 days.

FAI Record File Num #8520 [Direct Link]
Status: ratified – retired by changes of the sporting code
Region: World
Class: C (Powered Aeroplanes)
Sub-Class: C-1 (Landplanes)
Category: Not applicable
Group: 3 : turbo-jet
Type of record: Time to climb to a height of 30 000 m
Performance: 3 min 27.799s
Date: 1975-02-01
Course/Location: Grand Forks, ND (USA)
Claimant Roger J. Smith (USA)
Aeroplane: McDonnell Douglas F-15
Engines: 2 Pratt & Whitney F-100

Streak Eagle, the modified McDonnell Douglas F-15A-6-MC, 72-0119, on the runway at Grand Forks AFB, North Dakota, being prepared for a flight record attempt. (U.S. Air Force)

The flight profiles for the record attempts were developed by McDonnell Douglas Chief Developmental Test Pilot, Charles P. “Pete” Garrison (Lieutenant Colonel, U.S. Air Force, Retired).

Streak Eagle carried only enough fuel for each specific flight. It was secured to the hold-back device on the runway and the engines were run up to full afterburner. It was released from the hold-back and was airborne in just three seconds.

Screen Shot 2016-01-15 at 21.10.22 When the F-15 reached 428 knots (793.4 kilometers per hour), the pilot pulled up into an Immelmann turn, holding 2.5 Gs. Streak Eagle would arrive back over the air base in level flight at about 32,000 feet (9,754 meters), but upside down. Rolling right side up, Streak Eagle continued accelerating to Mach 1.5 while climbing through 36,000 feet (10,973 meters). It would then accelerate to Mach 2.2 and the pilot would pull the fighter up at 4.0 Gs until it reached a 60° climb angle. He held 60° until he had to shut down the engines to prevent them from overheating in the thin high-altitude atmosphere.

After reaching a peak altitude and slowing to just 55 knots (63 miles per hour, 102 kilometers per hour), the airplane was pushed over into a 55° dive. Once it was below 55,000 feet (16,764 meters) the engines would be restarted and Streak Eagle returned to land at Grand Forks.

McDonnell Douglas F-15A-6-MC 72-0119 Streak Eagle, Aquila Maxima, world record holder. (U.S. Air Force)

Streak Eagle is a very early production F-15A-6-MC Eagle, a single-seat, twin-engine air superiority fighter. It is 63 feet, 9.0 inches (19.431 meters) long with a wingspan of 42 feet, 9.7 inches (13.048 meters) and overall height of 18 feet, 5.4 inches (5.624 meters). The F-15A has an empty weight of 25,870 pounds (11,734 kilograms) and its maximum takeoff weight (MTOW) is 44,497 pounds (20,184 kilograms).

The F-15A is powered by two Pratt & Whitney JTF22A-25A (F100-PW-100) afterburning turbofan engines. The F100 is a two-spool, axial-flow turbine engine with a 3-stage fan section; 10-stage compressor; single chamber combustion section; and 4-stage turbine (2 low- and 2 high-pressure stages). The engine has a Maximum Continuous Power rating of 12,410 pounds of thrust (55.202 kilonewtons); 14,690 pounds (65.344 kilonewtons, 30-minute limit; and a maximum 23,840 pounds (106.046 kilonewtons), 5-minute limit. The F100-PW-100 is 191 inches (4.851 meters) long, 46.5 inches (1.181 meters) in diameter, and weighs 3,035 pounds (1,376.7 kilograms).

The cruise speed of the F-15A Eagle is 502 knots (578 miles per hour/930 kilometers per hour). It has a maximum speed of 893 knots (1,028 miles per hour/1,654 kilometers per hour) at 10,000 feet (3,048 meters), and 1,434 knots (1,650 miles per hour/2,656 kilometers per hour) at 45,000 feet (13,716 meters). The ceiling is 63,050 feet (19,218 meters) at maximum power. It can climb at an initial 67,250 feet per minute (342 meters per second) from Sea Level, and with a thrust-to-weight ratio of 1.15:1, The F-15 can climb straight up. The Eagle’s combat radius is 638 nautical miles (734 statute miles/1,182kilometers).

The F-15A is armed with one General Electric M61A1 Vulcan 20mm rotary cannon with 938 rounds of ammunition, four AIM-7 Sparrow radar-guided missiles and four AIM-9 Sidewinder heat-seeking missiles.

384 F-15A Eagles were built before production shifted to the improved F-15C version. As F-15Cs became operation, the F-15As were transferred to Air National Guard units assigned to defend continental U.S. airspace. The last F-15A was retired from service in 2009.

McDonnell Douglas F-15A-6-MC Streak Eagle 72-0119. (U.S. Air Force)

Streak Eagle was specially modified for the record attempts. Various equipment that would not be needed for these flights was eliminated: The flap and speed brake actuators, the M61A1 Vulcan 20 mm cannon and its ammunition handling equipment, the radar and fire control systems, unneeded cockpit displays and radios, and one generator.

Other equipment was added: A long pitot boom was mounted at the nose with alpha and beta vanes, equipment for the pilot’s David Clark Company A/P-225-6 full pressure suit, extremely sensitive accelerometers and other instrumentation, extra batteries, an in-cockpit video camera aimed over the pilot’s shoulder, and perhaps most important, a special hold-down device was installed in place of the fighter’s standard arresting hook.

These changes resulted in an airplane that was approximately 1,800 pounds (817 kilograms) lighter than the standard production F-15A. This gave it a thrust-to-weight ratio of 1.4:1.

Because Streak Eagle was a very early production airplane its internal structure was weaker than the final production F-15A standard. It was considered too expensive to modify it to the new standard, so it was transferred to the National Museum of the United States Air Force at Wright-Patterson Air Force Base, Ohio, in December 1980.

McDonnell Douglas F-15A-6MC 72-0119, “Streak Eagle,” at the National Museum of the United States Air Force. (U.S. Air Force 240528-F-IO108-055)
Roger J. Smith, 1951

Roger Jameson Smith was born 26 January 1935 at Fostoria, Ohio. He was the son of Ruland Leslie Smith, an illuminating engineer for a glass works, and Frances Victora Shaw Smith. He attended Newark High School, Newark, Ohio, graduating in 1953.

Following high school, Smith studied at Ohio State University. He was a member of the Reserve Officers Training Corps (R.O.T.C.), the Alpha Tau Omega (ΑΤΩ) fraternity, Pi Tau Sigma (ΠΤΣ) and  the Tau Beta Pi (ΤΒΠ) engineering honor societies. He graduated in 1958 with a degree in mechanical engineering. He later earned a masters degree from the University of Southern California.

Roger Smith was commissioned as a second lieutenant in the United States Air Force Reserve in October 1958. He then trained as a pilot.

Miss Marilyn Ann Dickey

Second Lieutenant Roger Jameson Smith married Miss Marilyn Ann Dickey at 6:30 p.m., Saturday, 6 June 1959, Weaver Memorial Chapel at Wittenberg College, Springfield, Ohio. The ceremony was presided over by Rev. Dr. Edgar F. Drumel. They would eventually have three children.

Smith deployed to Germany for two operational tours. He served in Southeast Asia during the Vietnam War. In 1967, he flew 75 combat missions from Bien Hoa Air Base, Republic of South Vietnam, in the Cessna A-37 Dragonfly, then 128 missions in the Republic F-105D Thunderchief from Takhli Royal Thai Air Force Base, Thailand.

Smith graduated from the U.S. Air Force Aerospace Research Test Pilot School at Edwards Air Force Base in California. He also attended the United States Naval War College.

Roger J. Smith retired from the United States Air Force in 1984. He had flown more than 5,000 hours, and had been awarded the Distinguished Flying Cross, Bronze Star, and ten Air Medals. For his flights in Streak Eagle, Smith was awarded the Mackay Trophy.

Colonel Roger Jameson Smith, U.S. Air Force (Retired) died 24 April 2021 at the age of 86 years. His remains were interred at the Jacksonville National Cemetery, Jacksonville, Florida.

© 2025, Bryan R. Swopes

29 January 1936

Grumman F3F-1, Bu. No. 0211, s/n 274. (San Diego Air & Space Museum, Roger Bilstein Collection 00032)

29 January 1936: The first production Grumman F3F-1, Bureau of Aeronautics serial number (“Bu. No.”) 0211 (Grumman Model G-11, serial number 271), was delivered to the United States Navy at NAS Anacostia, Washington, D.C. The F3F series was the last biplane fighter in service with the U.S. Navy.

The production F3F-1 aircraft were preceded by three XF3F-1 prototypes. Interestingly, all three prototypes had the same Grumman serial number, 257, and were assigned Bu. No. 9727. Two of these crashed.

The F3F-1 was built by the Grumman Aircraft and Engineering Corporation at Farmingdale, New York, in factory space rented from Fairchild Aircraft Company. It was a single-bay wire-braced biplane with manually-operated retractable landing gear and an enclosed cockpit with a sliding canopy. It had an arresting hook for landing aboard aircraft carriers.

The airplane had an aluminum monocoque fuselage with fabric covered wings, ailerons, rudder and elevators. The vertical fin and horizontal stabilizer were of metal construction. The ailerons were positioned on the upper wing. The wings for the F3F-1 and F3F-2 were built by the Brewster Aeronautical Corporation under a subcontract.

Grumman F3F-1 Bu. No. 0264. (U.S. Navy, Naval History and Heritage Command, 80-G-462080)

The F3F-1 was 23 feet, 3½ inches (7.099 meters) long. The upper wing had a span of 32 feet (9.754 meters) and a chord of 5 feet (1.524 meters). The lower wing’s span was 29 feet, 6 inches (8.992 meters) with a 4 foot (1.219 meters) chord. The total wing area was 260.6 square feet (24.2105 square meters). Both wings used a NACA CYH airfoil. The upper wing had no dihedral, but the lower wing had 2° dihedral. The vertical gap between the wings was 5 feet (1.524 meters) and the wings were staggered 2 feet, 7-1/16 inches (0.7889875 meters). The aircraft had an overall height of 10 feet, 6 inches (3.200 meters) with the thrust line level, and 8 feet 6 inches (2.591 meters) in three point attitude (not including the propeller).

Grumman F3F1 Bu. No. 0259, assigned to Fighting Squadron Three (VF-3). (U.S. Navy)

The F3F-1 was powered by an air-cooled, supercharged, 1,534.94-cubic-inch-displacement (25.153 liters) Pratt & Whitney R-1535-84 Twin Wasp Junior. This was a two-row, 14-cylinder radial engine, with a compression ratio of 6.75:1, requiring 87-octane gasoline. The direct drive engine turned a two-blade adjustable pitch Hamilton Standard propeller. The R-1535-84 was rated at 650 horsepower at 2,200 r.p.m. at 7,500 feet (2,286 meters), and 700 horsepower at 2,250 r.p.m. for takeoff. It was 3 feet, 8-1/8 inches (1.1208 meters) long, 3 feet, 6-3/8 inches (1.107 meters) in diameter, and weighed 959 pounds (434 kilograms).

The F3F-1 had a fuel capacity of 110 U.S. gallons (416 liters) in a 75 gallon (284 liter) main, and 35 gallon (132 liter) auxiliary tank. Its gross weight was 4,116 pounds (1,867 kilograms).

The F3F series was armed with one M1919 .30-caliber Browning machine gun with 500 rounds of ammunition, and one M2 .50-caliber Browning machine gun with 200 rounds. It could also carry a 110 pound (50 kilogram) bomb on a centerline bomb rack.

The F3F-1 had a maximum speed of 231 miles per hour (372 kilometers per hour) at 7,500 feet (2,286 meters). It could climb at 1,900 feet per minute (9.65 meters per second) and had a service ceiling of 29,500 feet (8,992 meters).

Flight of three Grumman F3F-1 from Fighting Squadron Four (VF-4), “The Red Rippers.” Note the gun cameras mounted on the upper wing. (SDA&SM Catalog # 16_003713)

The U.S. Navy ordered 54 F3F-1 fighters in August 1935. The final airplane in this series was modified to the XF3F-2, substituting a Wright Cyclone XR-1820-22 engine, rated at 850 horsepower at 2,100 r.p.m., and 950 horsepower at 2,200 r.p.m. for takeoff. This engine installation reduced the length of the airplane to 23 feet, 1-5/8 inches (7.052 meters).

A total of 147 F3F-1, -2 and -3 fighters were built. The type was retired in 1943.

The first F3F-1, Bu. No. 0211, crashed at sea near NAS Miami in March 1942.

Grumman F3F-1, Bu. No. 0252, assigned to Fighting Squadron Four (VF-4). The airplane is shown with the canopy open. (U.S. Navy)

© 2025, Bryan R. Swopes

27 January 1939

Lockheed XP-38 Lightning 37-457 at March Field, Riverside County, California, January 1939. (San Diego Air and Space Museum)
Lockheed XP-38 Lightning 37-457, 22 May 1941. (San Diego Air and Space Museum Archive)

27 January 1939: First Lieutenant Benjamin Scovill Kelsey, Air Corps, United States Army, made the first flight of the prototype Lockheed XP-38 Lightning, serial number 37-457, at March Field, Riverside County, California.

This was a short flight. Immediately after takeoff, Kelsey felt severe vibrations in the airframe. Three of four flap support rods had failed, leaving the flaps unusable.

1st Lieutenant Benjamin Scovill Kelsey, Air Corps, United States Army, 1937.

Returning to March Field, Kelsey landed at a very high speed with a 18° nose up angle. The tail dragged on the runway. Damage was minor and the problem was quickly solved.

Designed by an engineering team led by Hall L. Hibbard, which included the legendary Clarence L. “Kelly” Johnson, the XP-38 was a single-place, twin-engine fighter designed for very high speed and long range. It was an unusual configuration with the cockpit and armament in a center nacelle, with two longitudinal booms containing the engines and propellers, turbochargers, radiators and coolers. The Lightning was equipped with tricycle landing gear. The nose strut retracted into the center nacelle and the two main gear struts retracted into bays in the booms. To reduce drag, the sheet metal used butt joints with flush rivets.

The prototype had been built built at Lockheed’s factory in Burbank, California. On the night of 31 December 1938/1 January 1939, it was transported to March Field aboard a convoy of three trucks. Once there, the components were assembled by Lockheed technicians working under tight security.

Lockheed XP-38 Lightning 37-457. (San Diego Air and Space Museum)
Lockheed XP-38 Lightning 37-457. (San Diego Air and Space Museum Archive)
Lockheed XP-38 Lightning 37-457. (San Diego Air and Space Museum Archive)
Left profile, Lockheed XP-38 Lightning 37-457. (U.S. Air Force)
Left profile, Lockheed XP-38 Lightning 37-457. (U.S. Air Force)
Lockheed XP-38 Lightning 37-457

The XP-38 was 37 feet, 10 inches (11.532 meters) long with a wingspan of 52 feet (15.850 meters) and overall height of 12 feet, 10 inches (3.952 meters). Its empty weight was 11,507 pounds (5,219.5 kilograms). The gross weight was 13,904 pounds (6,306.75 kilograms) and maximum takeoff weight was 15,416 pounds (6,992.6 kilograms).

The Lightning was the first production airplane to use the Harold Caminez-designed, liquid-cooled, supercharged, 1,710.60-cubic-inch-displacement (28.032 liter) Allison Engineering Company V-1710 single overhead cam 60° V-12 engines. When installed on the P-38, these engines rotated in opposite directions. The XP-38 used a pair of experimental C-series Allisons, with the port V-1710-C8 (V-1710-11) engine being a normal right-hand tractor configuration, while the starboard engine, the V-1710-C9 (V-1710-15), was a left-hand tractor. Through a 2:1 gear reduction, these engines drove the 11-foot (3.353 meters) diameter, three-bladed Curtiss Electric variable-pitch propellers inward to counteract the torque effect of the engines and propellers. (Viewed from the front of the airplane, the XP-38’s starboard propeller turned clockwise, the port propeller turned counter-clockwise. The direction of rotation was reversed in the YP-38 service test prototypes and production P-38 models.) The engines have long propeller gear drive sections to aid in streamlining aircraft, and are sometimes referred to as “long-nose Allisons.”

The V-1710-11 and -15 had a compression ratio of 6.65:1. They had a continuous power rating of 1,000 horsepower at 2,600 r.p.m. at Sea Level, and 1,150 horsepower at 2,950 r.p.m. for takeoff. The combination of a gear-driven supercharger and an exhaust-driven General Electric B-1 turbosupercharger allowed these engines to maintain their rated power levels to an altitude of 25,000 feet (7,620 meters).

The -11 and -15 were 7 feet, 10.46 inches (2.399 meters) long. The -11 was 3 feet, 6.59 inches (1.082 meters) high and 2 feet, 4.93 inches (0.7348 meters) wide. It weighed 1,300 pounds (589.7 kilograms). The -15 was 3 feet, 4.71 inches (1.034 meters) high, 2 feet, 4.94 inches (0.7351 meters) wide, and weighed 1,305 pounds (591.9 kilograms).

A 1939 Allison Engine Company V-1710-33 liquid-cooled, supercharged SOHC 60° V-12 aircraft engine at the Smithsonian Institution National Air and Space Museum. This engine weighs 1,340 pounds (607.8 kilograms) and produced 1,040 horsepower at 2,800 r.p.m. During World War II, this engine cost $19,000. (NASM)
A 1939 Allison Engine Company V-1710-33 liquid-cooled, supercharged SOHC 60° V-12 aircraft engine at the Smithsonian Institution National Air and Space Museum. This engine weighs 1,340 pounds (607.8 kilograms) and produced 1,040 horsepower at 2,800 r.p.m. During World War II, this engine cost $19,000. (NASM)

The XP-38 had a maximum speed of 413 miles per hour (664.66 kilometers per hour) at 20,000 feet (6,096 meters) and a service ceiling of 38,000 feet (11,582.4 meters).

The XP-38 was unarmed, but almost all production Lightnings carried a 20 mm auto cannon and four Browning .50-caliber machine guns grouped together in the nose. They could also carry bombs or rockets and jettisonable external fuel tanks.

Lockheed XP-38 37-457. (San Diego Air and Space Museum Archive)
Lockheed XP-38 37-457. (San Diego Air and Space Museum Archive)

The prototype XP-38 was damaged beyond repair when, on approach to Mitchel Field, New York, 11 February 1939, both engines failed to accelerate from idle due to carburetor icing. Unable to maintain altitude, Lieutenant Kelsey crash landed on a golf course and was unhurt.

Testing continued with thirteen YP-38A pre-production aircraft and was quickly placed in full production. The P-38 Lightning was one of the most successful combat aircraft of World War II. By the end of the war, Lockheed had built 10,037 Lightnings.

Lockheed test pilot Tony LeVier in the cockpit of P-38J-10-LO Lightning 42-68008. (Lockheed Martin)

© 2019, Bryan R. Swopes

24 January 1962

Sanford N. ("Sandy") McDonnell hands over the keys to the first F-110A Spectre to the United States Air Force, St. Louis, Missouri, 24 January 1962. (McDonnell Aircraft Corporation)
Sanford N. (“Sandy”) McDonnell hands over the keys to the first F-110A Spectre to the United States Air Force, St. Louis, Missouri, 24 January 1962. (McDonnell Aircraft Corporation)

24 January 1962: The McDonnell Aircraft Corporation delivered the first F-110A Spectre to Colonel Gordon Graham and Colonel George Laven, United States Air Force, at the McDonnell plant at St. Louis, Missouri. The F-110A was soon redesignated as the F-4C Phantom II.

Two Phantoms were delivered to the Air Force for evaluation at Langley Field, Virginia. They were U.S. Navy F4H-1 Phantom IIs, Bureau of Aeronautics serial numbers 149405 and 149406. Initially the aircraft retained the Navy serial numbers but eventually were assigned Air Force numbers 62-12168 and 62-12169. The Air Force bailed them back to McDonnell to develop the YF-4C prototypes.

62-12169 (ex-Bu. No. 149406) was converted to a JF-4B (a special test aircraft). Operated by the McDonnell-Douglas Aircraft Center at Holloman Air Force Base, New Mexico, it suffered an engine explosion, 8 March 1967. McDonnell test pilot Charles (“Pete”) Garrison successfully ejected. The airplane crashed and was destroyed.

McDonnell Aircraft Corporation F-110A Spectre 149405. (McDonnell Aircraft Corporation)
McDonnell Aircraft Corporation F-110A Spectre 149405. (McDonnell Aircraft Corporation)
U.S. Air Force F-110A Spectre with bomb load.
U.S. Air Force F-110A Spectre 149405 armed with AIM-101 Sparrow missiles and Mk.82 500-pound bombs. (McDonnell Aircraft Corporation)
U.S. Air Force F-110A Spectre 149405 armed with AIM-101 Sparrow missiles and Mk.82 500-pound bombs. (NARA)

McDonnell built 5,057 Phantom IIs. They served with the United States Navy and Marine Corps, the U.S. Air Force, and many allied nations. The last Phantom II, an F-4E, was completed 25 October 1979. The U.S. Air Force retired its last operational Phantoms from service 20 December 2004, 42 years, 10 months, 27 days after receiving the first F-110A.

McDonnell F-110A Spectre 149405 (F4H-1, F-4B-9i, and F-4C-15-MC 62-12168).
McDonnell F-110A Spectre 149405 (F4H-1, F-4B-9i-MC, and finally, F-4C-15-MC 62-12168). (McDonnell Aircraft Corporation)
McDonnell F-110A 149406 at Nellis Air Force Base, March 1962. (NARA)
McDonnell F-4C-15-MC Phantom IIs 149405 and 149406, circa 1963. (NARA)
McDonnell F-110A 149405 and 149406 in formation near Lambert Field, St. Louis, Missouri. (NARA)

© 2018, Bryan R. Swopes

14 January 1950

This is the second Mikoyan Gurevich I 330 prototype, SI 02.
This is the second Mikoyan Gurevich I 330 prototype, SI 02.

14 January 1950: The Mikoyan Gurevich prototype fighter I 330 SI made its first flight with test pilot Ivan Ivashchenko. It would be developed into the MiG 17.

The MiG 17 was an improved version of the earlier MiG 15. It was a single-seat, single engine fighter armed with cannon, and capable of high subsonic and transonic speed.

Mikoyan Gurevich MiG 17.
Mikoyan Gurevich MiG 17.

The prototype’s wings were very thin and this allowed them to flex. The aircraft suffered from “aileron reversal,” in that the forces created by applying aileron to roll the aircraft about its longitudinal axis were sufficient to bend the wings and that caused the airplane to roll in the opposite direction.

The first prototype I 330 SI developed “flutter” while on a test flight, 17 March 1950. This was a common problem during the era, as designers and engineers learned how to build an airplane that could smoothly transition through the “sound barrier.” The rapidly changing aerodynamic forces caused the structure to fail and the horizontal tail surfaces were torn off. The prototype went into an unrecoverable spin. Test pilot Ivashchenko was killed.

Two more prototypes, SI 02 and SI 03, were built. The aircraft was approved for production in 1951.

More than 10,000 MiG 17 fighters were built in the Soviet Union, Poland and China. The type remains in service with North Korea.

A MiG 17 in flight.
A MiG 17 in flight.
Иван Т. Иващенко летчик-испытатель
Иван Т. Иващенко летчик-испытатель

Ива́н Тимофе́евич Ива́щенко (Ivan T. Ivashchenko) was born at Ust-Labinsk, Krasnodar Krai, Russia, 16 October 1905. He served in the Red Army from 1927 to 1930. He graduated from the Kuban State University in 1932.

Ivashchenko was trained as a pilot at the Lugansk Military Aviation School at Voroshilovgrad, and a year later graduated from the Kachin Military Aviation College at Volgograd.

In 1939, he fought in The Winter War. During the Great Patriotic War, Ivan Ivashchenko flew with a fighter squadron in the defense of Moscow.

From 1940 to 1945, Ivan Ivashchenko was a test pilot. He trained at the M.M. Gromov Flight Research Institute at Zhokovsky, southeast of Moscow, in 1941. He was assigned to Aircraft Factory No. 18 at Kuibyshev (Samara) from 1941 to 1943. Ivashchenko flew the Ilyushin Il-2 Sturmovik fighter bomber extensively. From 1943 to 1945 he was a test pilot for Lavochkin OKB at Factory 301 in Khimki, northwest of Moscow.

In 1945 Ivashchenko was reassigned to OKB Mikoyan, where he worked on the development of the MiG 15 and MiG 17 fighters. He participated in testing ejection seat systems and in supersonic flight.

Ivan T. Ivashchenko was a Hero of the Soviet Union, and was awarded the Order of Lenin, Order of the Red Banner (two awards) and Order of the Patriotic War. Killed in the MiG 17 crash at the age of 44 years, he was buried at the Novodevichy Cemetery in Moscow.

© 2017, Bryan R. Swopes