Jacqueline Auriol in the cockpit of a SNCASE SE.535 Mistral. (Maurice Jarnoux/Paris Match)
21 December 1952: Flying a Société nationale des constructions aéronautiques du Sud-Est-built DH.100 Mistral powered by a Rolls-Royce Nene 104 turbojet engine, Mme Jacqueline Marie-Thérèse Suzanne Douet Auriol set a Fédération Aéronautique Internationale (FAI) World Record for Speed Over 100 Kilometers Without Payload of 855,92 kilometers per hour (531.84 miles per hour).¹
A SNCASE DH.100 Vampire. (National Archives at College Park, National Archives Identifier 19982005)
Jacqueline Auriol Sets New Record
MARSEILLE, France, Dec. 21 (AP)—Jacqueline Auriol, daughter-in-law of the French president, today bettered her own woman’s record for flying over a closed 100-kilometer (62.13 mile) course with an average time of 534.375 miles an hour.
Mrs. Auriol’s flight today beat the record of 511.360 miles an hour which she set in May, 1951. She flew a “Mistral” jet fighter of the French nationalized aircraft industry, powered by a Nene-Hispano Suiza motor. The previous record had been set with a jet “Vampire.”
In three passes at the course from Istre military base north of Marseille to Avignon and return, Mrs. Auriol bettered her record on the second try.
She is the wife of Paul Auriol, son and secretary of the president of the French Republic.
This Day in Aviation has not been able to determine with certainty the exact variant of the SNCASE Mistral that Mme Auriol flew to set this record. The FAI’s online database identifies the aircraft as a “DH.100 Mistral,” but powered by a Rolls-Royce Nene 104 engine. Most contemporary newspaper articles identify the aircraft only as a “Mistral,” and a few, as a “Mistral 76.” So, some speculation is in order.
Initially, Société nationale des constructions aéronautiques du Sud-Est (SNCASE) produced the de Havilland DH.100 Vampire for the Armée de l’air from kits supplied by de Havilland. It went to on to build Vampires based on the FB.5 fighter bomber airframe. SNCASE then developed its own variant, the SE.530 Mistral, which used a Hispano-Suiza-built Rolls-Royce Nene 102 turbojet engine in place of the Vampire’s de Havilland Goblin. (De Havilland designated these fighter bombers as the FB.53 Mistral.) Four SE.530 prototypes were built, followed by 93 production SE.532s. This was further upgraded to the SE.535, which featured enlarged air intakes for the Nene 104 engine, a pressurized cockpit, and a SNCASO ejection seat. It also had an increased fuel capacity. The SE.532s were upgraded to the SE.535 standard. SNCASE built 150 SE.535s.
The 1952 photograph at the head of this article shows Mme Auriol seated in a Mistral with the number 76 painted on its fuselage. Could this be the “Mistral 76” mentioned in the newspaper articles?
Does the number 76 identify this airframe as the 76th of the 93 SE.532s? Since the FAI database states that the engine is a Nene 104, can we further speculate that this 532 has been upgraded to the SE.535 standard?
A French website, FRROM, states that the Mistral flown by Mme Auriol to set the 21 December 1952 speed record was later assigned to 7th Escadres de Chase.
21 December 1916: Harry George Hawker, M.B.E., A.F.C., made the first flight of the Sopwith Camel at Brooklands Aerodrome, Surrey, England. This airplane would become the Royal Air Force’s most successful fighter of World War I.
The Sopwith Camel F.1 was a British single-place, single-engine biplane fighter, produced by the Sopwith Aviation Co., Ltd., Canbury Park Road, Kingston-on-Thames. The airplane was constructed of a wooden framework, with the forward fuselage being covered with aluminum panels and plywood, while the aft fuselage, wings and tail surfaces were covered with fabric.
The length of the Camel F.1 varied from 18 feet, 6 inches (5.639 meters) to 19 feet, 0 inches (5.791 meters), depending on which engine was installed. Both upper and lower wings had a span of 28 feet, 0 inches (8.534 meters) and chord of 4 feet, 6 inches (1.372 meters). They were separated vertically by 5 feet (1.524 meters) at the fuselage. The upper wing had 0° dihedral, while the lower wing had 5° dihedral and was staggered 1 foot, 6 inches (0.457 meters) behind the upper wing. The single-bay wings were braced with airfoil-shaped streamline wires. The overall height of the Camel also varied with the engine, from 8 feet, 6 inches (2.591 meters) to 8 feet, 9 inches (2.667 meters).
The heaviest Camel F.1 variant used the Le Rhône 180 h.p. engine. It had an empty weight of 1,048 pounds (475 kilograms). Its gross weight of 1,567 pounds (711 kilograms). The lightest was equipped with the Gnôme Monosoupape 100 horsepower engine, with weights of 882 pounds (400 kilograms) and 1,387 pounds (629 kilograms), respectively.
Front view of a Sopwith Camel F.I (Unattributed)
The first Camel was powered by an air-cooled 15.268 liter (931.72 cubic inches) Société Clerget-Blin et Cie Clerget Type 9 nine-cylinder rotary engine which produced 110 horsepower at 1,200 r.p.m. and drove a wooden two-bladed propeller. Eight different rotary engines ¹ from four manufacturers, ranging from 100 to 180 horsepower, were used in the type.
The best performance came with the Bentley B.R.1 engine (5.7:1 compression ratio). This variant had a maximum speed of 121 miles per hour (195 kilometers per hour) at 10,000 feet (3,048 meters), and 114.5 miles per hour (184 kilometers per hour) at 15,000 feet (4,572 meters). It could climb to 6,500 feet (1,981 meters) in 4 minutes, 35 seconds; to 10,000 feet (3,048 meters) in 8 minutes, 10 seconds; and 15,000 feet (4,572 meters) in 15 minutes, 55 seconds. It had a service ceiling of 22,000 feet (6,706 meters). Two other Camel variants could reach 24,000 feet (7,315 meters).
The Bentley B.R.1 rotary engine was designed by Lieutenant Walter Owen Bentley, Royal Naval Air Service (later, Captain, Royal Air Force), based on the Clerget Type 9, but with major improvements. It used aluminum cylinders shrunk on to steel liners, with aluminum pistons. The Bentley B.R.1 (originally named the Admiralty Rotary, A.R.1, as it was intended for use by the Royal Navy) was an air-cooled, normally-aspirated 17.304 liter (1,055.948 cubic inches) right-hand tractor, nine-cylinder rotary engine with a compression ratio of 5.7:1. It was rated at 150 horsepower at 1,250 r.p.m. The B.R.1 was 1.110 meters (3 feet, 7.7 inches) long, 1.070 meters (3 feet, 6.125 inches) in diameter and weighed 184 kilograms (406 pounds.) The engine was manufactured by Humber, Ltd., Coventry, England, and Vickers, Ltd., Crayford.
The instruments and armament of a Sopwith Camel from No. 4 Squadron, AFC. (Australian War Memorial)
The Camel was armed with two fixed, forward-firing .303-caliber (7.7×56mmR) Vickers machine guns, synchronized to fire forward through the propeller. These guns were modified for air cooling. Some night fighter variants substituted Lewis machine guns mounted above the upper wing for the Vickers guns. Four 25 pound (11.3 kilogram) bombs could be carried on racks under the fuselage.
The Sopwith Camel was a difficult airplane to fly. Most of its weight was concentrated far forward, making it unstable, but, at the same time making the fighter highly maneuverable. The rotary engine, with so much of its mass in rotation, caused a torque effect that rolled the airplane to the right to a much greater degree than in airplanes equipped with radial or V-type engines. A skilled pilot could use this to his advantage, but many Camels ended upside down while taking off.
Major William G. Barker, RAF, with an upside-down Sopwith Camel F.1 of No. 28 Squadron, Italy, 1918. (Library and Archives Canada)
Twelve manufacturers ² produced 5,490 Sopwith Camels between 1916 and 1920. By the end of World War I, it was becoming outclassed by newer aircraft, however it was the single most successful fighter of the war, shooting down 1,294 enemy aircraft.
One single fighter, Major William Barker’s Sopwith Aviation Co., Ltd., Camel F.1 B.6313 shot down 46 enemy aircraft, more than any other fighter in history.
It is believed that only seven Sopwith Camels still exist.
Wing Commander William George Barker, V.C., D.S.O. with Bar, M.C. with 2 Bars, Croix de Guerre, with his Sopwith Camel F.1. (Library and Archives Canada)
20th Fighter Squadron McDonnell Douglas F-4F-54-MC Phantom 72-1150, with another F-4F banking away, over the skies of New Mexico. (U.S. Air Force)
20 December 2004: The 20th Fighter Squadron, 49th Fighter Wing, Holloman Air Force Base, New Mexico, the last operational squadron in the United States Air Force flying the McDonnell Douglas F-4 Phantom II, was inactivated. The squadron’s F-4F fighters were sent to The Boneyard at Davis-Monthan Air Force Base, Tucson, Arizona.
Row after row of F-4 Phantom II fighters in storage at Davis-Monthan AFB, near Tucson, Arizona.
Senior Lieutenant Nguyễn Văn Cốc in the cockpit of a MiG 21. (From the collection of CMSGT Bob Laymon, USAF)
20 December 1969: Senior Lieutenant Nguyễn Văn Cốc, of the 921st Fighter Regiment, Vietnam Peoples’ Air Force, flying a Mikoyan-Gurevich Mig 21PFL supersonic interceptor, shot down his final enemy aircraft of the Vietnam War, a U.S. Air Force AQM-34L reconnaissance drone (Ryan Aeronautical Company Model 147SC, code named BUFFALO HUNTER).
A U.S. Air Force Ryan AQM-34L Buffalo Hunter of the 556th Reconnaissance Squadron, based at Bien Hoa Air Base, circa 1969. This drone flew 68 missions before being shot down over Hanoi. (U.S. Air Force)
Nguyễn Văn Cốc entered the Không quân Nhân dân Việt Nam (Vietnamese People’s Air Force) in 1961. He spent four years in the Soviet Union training as a fighter pilot, and was qualified on both the Mikoyan-Gurevich MiG 17 and MiG 21.
Nguyễn was credited by the VPAF with nine aerial combat victories. Seven of these were also confirmed by the United States. Between 30 April 1967 and 20 December 1969, he shot down a Convair F-102A Delta Dart, three Republic F-105D Thunderchiefs, one F-105F Thunderchief, a McDonnell F-4B Phantom II, two F-4D Phantom IIs, and the BUFFALO HUNTER.
Senior Lieutenant Nguyễn Văn Cốc, at right, with two other pilots. A Mikoyan-Gurevich MiG 21PF is in the background. (VPAF)
All of Nguyễn’s victories were scored while flying the MiG 21PFL, with R-3S infrared-homing air-to-air missiles.
These MiG 21s are assigned to the 921st Fighter Regiment. The closest, “Red 4326,” is one of the interceptors flown by Nguyễn Văn Cốc. The 13 “kill marks” on its nose represent enemy aircraft shot down by Nguyễn and other pilots who flew the airplane. This airplane is on display at the Hanoi Air Defense Museum (Bảo tàng Phòng không-Không quân). (VPAF)
The R-3S (also known as the K-13, and identified as “AA-2A Atoll” by NATO forces) was reverse-engineered by the Turopov Design Bureau, Tushino, Russia, from a Raytheon AIM-9B Sidewinder which had been captured by the People’s Republic of China during the 1958 Taiwan Straits Crisis. Fired by a Republic of China Air Force F-86 Sabre, the missile hit a People’s Liberation Army Air Force MiG 17, but its warhead did not detonate. The PLAAF turned the Sidewinder over to the Soviet Union.
Lieutenant General Nguyễn remained in the VPAF until retiring in 2002 with the rank of chief inspector. He is the highest-scoring fighter pilot of the Vietnam War.
Captain Nguyễn Văn Cốc is congratulated by Hồ Chí Minh, President of the Democratic Republic of Vietnam.
The BUFFALO HUNTER was approximately 26 feet (7.9 meters) long with a wing span of 13 feet (4.0 meters). It weighed 3,067 pounds (1,391 kilograms).
The drone was powered by a single Continental J69 turbojet engine, rated at 1,920 pounds of thrust (8.54 kilonewtons).
BUFFLO HUNTERS had a cruising speed of 500–540 knots (575–621 miles per hour/926-1,000 kilometers per hour), but could reach 590 knots (679 miles per hour/1,093 kilometers per hour) “on the deck.” It had a maximum range of 650 nautical miles (748 statute miles/1,204 kilometers).
The drone was equipped with a Fairchild 415Y reconnaissance camera. It carried 1,800 feet (549 meters) of 70-millimeter film.
BUFFALO HUNTERs were launched by Lockheed DC-130 drone carriers, modified from C130 A or -E Hercules transports. Most carried two drones on underwing pylons, but two of the DC-130s could carry four.
A Lockheed DC-130 carrying two BUFFALO HUNTER reconnaissance drones. (U.S. Air Force)
North American Aviation, Inc., X-15A-1, 56-6670, at Los Angeles Division, October 1958. (Air Force Flight Test Center History Office)
20 December 1968: After 199 flights, the National Aeronautics and Space Administration cancelled the X-15 Hypersonic Research Program. A 200th X-15 flight had been scheduled, but after several delays, the decision was made to end the program. (The last actual flight attempt was 12 December 1968, but snow at several of the dry lakes used as emergency landing areas resulted in the flight being cancelled.)
The X-15A rocketplane was designed and built for the U.S. Air Force and the National Advisory Committee for Aeronautics (NACA, the predecessor of NASA) by North American Aviation, Inc., to investigate the effects of hypersonic flight (Mach 5+). Design work started in 1955 and a mock-up had been completed after just 12 months. The three X-15s were built at North American’s Los Angeles Division, at the southeast corner of Los Angeles International Airport (LAX), on the shoreline of southern California.
The first flight took place 8 June 1959 with former NACA test pilot Albert Scott Crossfield in the cockpit of the Number 1 ship, 56-6670.
Scott Crossfield prepares for a flight in the North American Aviation X-15A.
While earlier rocketplanes, the Bell X-1 series, the the Douglas D-558-II, and the Bell X-2, were airplanes powered by rocket engines, the X-15 was a quantum leap in technology. It was a spacecraft.
Like the other rocketplanes, the X-15 was designed to be carried aloft by a “mothership,” rather than to takeoff and climb to the test altitude under its own power. The carrier aircraft was originally to be a Convair B-36 intercontinental bomber but this was soon changed to a Boeing B-52 Stratofortress. Two B-52s were modified to carry the X-15: NB-52A 52-003, The High and Mighty One, and NB-52B 52-008, Balls 8.
From 8 June 1959 to 24 October 1968, the three X-15s were flown by twelve test pilots, three of whom would qualify as astronauts in the X-15. Two would go on to the Apollo Program, and one, Neil Alden Armstrong, would be the first human to set foot on the surface of the Moon, 20 July 1969. Joe Engle would fly the space shuttle. Four of the test pilots, Petersen, White, Rushworth, and Knight, flew in combat during the Vietnam War, with Bob White being awarded the Air Force Cross. Petersen, Rushworth and White reached flag rank.
One pilot, John B. (“Jack”) McKay, was seriously injured during an emergency landing at Mud Lake, Nevada, 9 November 1962. Another, Michael James Adams, was killed when the Number 3 ship, 56-6672, went into a hypersonic spin and broke up on the program’s 191st flight, 15 November 1967.
North American Aviation, Inc., X-15A-1 56-6670 on Rogers Dry Lake, Edwards Air Force Base, California. (NASA Image E-5251)
Flown by a single pilot/astronaut, the X-15 is a mid-wing monoplane with dorsal and ventral fin/rudders and stabilators. The wing had no dihdral, while the stabilators had a pronounced -15° anhedral. The short wings have an area of 200 square feet (18.58 square meters) and a maximum thickness of just 5%. The leading edges are swept to 25.64°. There are two small flaps but no ailerons. The entire vertical fin/rudder pivots for yaw control.
Above 100,000 feet (30,840 meters) altitude, conventional aircraft flight control surfaces are ineffective. The X-15 is equipped with a system of reaction control jets for pitch, roll and yaw control. Hydrogen peroxide was passed through a catalyst to produce steam, which supplied the control thrusters.
The forward landing gear consists of a retractable oleo strut with steerable dual wheels and there are two strut/skids at the rear of the fuselage. The gear is retracted after the X-15 is mounted on the NB-52 and is extended for landing by its own weight.
North American Aviation, Inc., X-15A-3 56-6672 just before touch down on Rogers Dry Lake. (NASA Image E-7469)
The rocketplane’s cockpit featured both a conventional control stick as well as side-controllers. It was pressurized with nitrogen gas to prevent fires. The pilot wore an MC-2 full-pressure suit manufactured by the David Clark Company of Worcester, Massachusetts, with an MA-3 helmet. The suit was pressurized below the neck seal with nitrogen, while the helmet was supplied with 100% oxygen. This pressure suit was later changed to the Air Force-standardized A/P22S.
X-15 cockpit with original Lear Siegler instrument panel. (NASA image E63-9834)
The X-15 is 50.75 feet (15.469 meters) long with a wing span of 22.36 feet (6.815 meters). The height—the distance between the tips of the dorsal and ventral fins—is 13.5 feet (4.115 meters). The stabilator span is 18.08 feet (5.511 meters). The fuselage is 4.67 feet (1.423 meters) deep and has a maximum width of 7.33 feet (2.234 meters).
Since the X-15 was built of steel rather than light-weight aluminum, as are most aircraft, it is a heavy machine, weighing approximately 14,600 pounds (6,623 kilograms) empty and 34,000 pounds (15,422 kilograms) when loaded with a pilot and propellants. The X-15s carried as much as 1,300 pounds (590 kilograms) of research instrumentation, and the equipment varied from flight to flight. The minimum flight weight (for high-speed missions): 31,292 pounds (14,194 kilograms) The maximum weight was 52,117 pounds (23,640 kilograms) at drop (modified X-15A-2 with external propellant tanks).
Initial flights were flown with a 5 foot, 11 inch (1.803 meters)-long air data boom at the nose, but this would later be replaced by the “ball nose” air sensor system. The data boom contained a standard pitot-static system along with angle-of-attack and sideslip vanes. The boom and ball nose were interchangeable.
NASA Research Test Pilot Neil A. Armstrong with the first North American Aviation X-15A, 56-6670, on Rogers Dry Lake after a flight, 1960. His right hand is resting on the rocketplane’s ball nose sensor. (NASA Image E60-6286)
The X-15s were built primarily of a nickel/chromium/iron alloy named Inconel X, along with corrosion-resistant steel, titanium and aluminum. Inconel X is both very hard and also able to maintain its strength at the very high temperatures the X-15s were subjected to by aerodynamic heating. It was extremely difficult to machine and special fabrication techniques had to be developed.
Delays in the production of the planned Reaction Motors XLR99 rocket engine forced engineers to adapt two vertically-stacked Reaction Motors XLR11-RM-13 four-chamber rocket engines to the X-15 for early flights. This was a well-known engine which was used on the previous rocketplanes. The XLR11 burned a mixture of ethyl alcohol and water with liquid oxygen. Each of the engines’ chambers could be ignited individually. Each engine was rated at 11,800 pounds of thrust (58.49 kilonewtons) at Sea Level.
Two Reaction Motors Division XLR11-RM-13 four-chamber rocket engines installed on an X-15. The speed brakes of the ventral fin are shown in the open position. (NASA)
The Reaction Motors XLR99-RM-1 rocket engine was throttleable by the pilot from 28,500 to 60,000 pounds of thrust (126.77–266.89 kilonewtons). The engine was rated at 50,000 pounds of thrust (222.41 kilonewtons) at Sea Level; 57,000 pounds (253.55 kilonewtons) at 45,000 feet (13,716 meters), the typical drop altitude; and 57,850 pounds (257.33 kilonewtons) of thrust at 100,000 feet (30,480 meters). Individual engines varied slightly. A few produced as much as 61,000 pounds of thrust (271.34 kilonewtons).
The XLR99 burned anhydrous ammonia and liquid oxygen. The flame temperature was approximately 5,000 °F. (2,760 °C.) The engine was cooled with circulating liquid oxygen. To protect the exhaust nozzle, it was flame-sprayed with ceramic coating of zirconium dioxide. The engine is 6 feet, 10 inches (2.083 meters) long and 3 feet, 3.3 inches (0.998 meters) in diameter. It weighs 910 pounds (413 kilograms). The Time Between Overhauls (TBO) is 1 hour of operation, or 100 starts.
The XLR99 proved to be very reliable. 169 X-15 flights were made using the XLR99. 165 of these had successful engine operation. It started on the first attempt 159 times.
The highest speed achieved during the program was with the modified number two ship, X-15A-2 56-6671, flown by Pete Knight to Mach 6.70 (6,620 feet per second/4,520 miles per hour/7,264 kilometers per hour) at 102,700 feet (31,303 meters). On this flight, the rocketplane exceeded its maximum design speed of 6,600 feet per second (2,012 meters per second).
The maximum altitude was reached by Joe Walker, 22 August 1963, when he flew 56-6672 to 354,200 feet (107,960 meters).
The longest flight was flown by Neil Armstrong, 20 April 1962, with a duration of 12 minutes, 28.7 seconds.
North American Aviation X-15A-1 56-6670 is on display at the Smithsonian Institution National Air and Space Museum. X-15A-2 56-6671 is at the National Museum of the United States Air Force.
A North American Aviation F-100 Super Sabre chase plane follows NB-52A 52-003 prior to launch of an X-15. (NASA)
Recommended reading:
Always Another Dawn: The Story of a Rocket Test Pilot, by A. Scott Crossfield and Clay Blair, Jr., The World Publishing Company, Cleveland and New York, 1960
At The Edge Of Space, by Milton O. Thompson, Smithsonian Institution Press, 1992
X-15 Diary: The Story of America’s First Spaceship, by Richard Tregaskis, E.F. Dutton & Company, New York, 1961; University of Nebraska Press, 2004
X-15: Exploring the Frontiers of Flight, by David R. Jenkins, National Aeronautics and Space Administration http://www.nasa.gov/pdf/470842main_X_15_Frontier_of_Flight.pdf
The X-15 Rocket Plane: Flying the First Wings into Space, by Michelle Evans, University of Nebraska Press, Lincoln and London, 2013
North American Aviation, Inc., X-15A-2 56-6671 accelerates after igniting its Reaction Motors XLR99-RM-1 rocket engine (NASA)
