Sin 1: Breguet 690 Series, Consolidated-Vultee XP-81, Curtiss XP-46, Curtiss XP-62, Curtiss XF14C-2, Vultee XP-54, Lockheed XP-58, Kawasaki Ki.60, Fiat C.R. 42.
Sin 2: Messerschmitt Bf 110, Brewster F2A Buffalo, Boeing XF8B, Bell P-39 Airacobra, Nakajima Ki.43 Hayabusa, Nakajima Ki. 44 Shoki, Focke-Wulf Fw 200, Loire 210, Westland Welkin, Fairey Fulmar.
Sin 3: Bell XP-83, Nakajima Ki.87, Tachikawa Ki.94 Berezniak-Isaev BI-1.
Sin 4: Hawker Tornado, Curtiss XP-60, Republic P-43 Lancer, Mikoyan-Gurevich MiG-3 Bloch MB-150 series, Potez 630 Series, Heinkel He 280, Westland Whirlwind, Blackburn Firebrand, Fiat G.50.
Sin 5: Commonwealth Woomera, Kyushu J7W1 Shinden, General motors P-75 Eagle, McDonnell XP-67, Northrop XP-56, Kawasaki Ki. 64, Kawanishi N1K1-J Shiden, Mitsubishi J2M2 Raiden, De Schelde S.21, Polikarpov I-16, Messerschmitt Me 210, Amiot 350 Series.
Sin 6: Horten Go 229, Mitsubishi Ki.46 Dinah, Commonwealth CA-12 Boomerang, V.L. Myrsky, Caudron C. 714, S.A.I. 207, Focke-Wulf Fw 187.
Sin 7: Curtiss XP-55 Ascender, Bachem Ba 349 Natter, Heinkel He 177, Blohm und Voss BV 141, Kawanishi E15K1 Shiun, Aichi M6A1 Seiran, Arado Ar 231, S.A.I. S.S.4, Piaggio P.119.
Is the Northrop XP-79 can be considered under Sin 7?
In September 1942 John Northrop proposed to the USAAF the construction of the MX-322 (XP-79), a rocket-powered point-defense interceptor with flying wing configuration and prone-pilot with glass
bubble nose. The airplane should be powered by an Aerojet XCAL R-2000 A-1 bi-propellant rocket engine, with 906 kgp (2,000 lbf) peak thrust, and was theoretically capable of reaching an altitude of 12,000 m (39,360 ft) and a maximum speed of 865 km/h (538 mph).
The prone position would permit greater maneuvering g-forces than a conventionally seated pilot and save the drag generated by a conventionally windshield/canopy ensemble. The proposed armament was four wing-mounted 0.50 cal Browning M-2 heavy machine guns, with 250 rounds per gun. The airframe was to be built of welded magnesium alloy and include 45-degrees angled, 20 mm thick plates to provide armor protection for the propellant tanks.
In many published reports the armored leading edge was misinterpreted as a collision tactics ramming device and the XP-79 was wrongly denominated
Flying Ram.
In the original blueprints the mock-up initially had a central fixed skid or a modified landing gear with two retractable skids, but it was replaced by four retractable legs with wheels in a later design (MX-365) in July 1943.
The XP-79 should use two GALCIT Jet Assisted Take Off solid fuel rockets, with 453 kgp (1,000 lbf) peak thrust each. The Aerojet engine employed two primary combustion chambers, with 339 kgp (748 lbf) peak thrust each, and two auxiliary chambers with 113 kgp (250 lbf) each.
The whole ensemble,
Rotojet, revolved to generate propellant pumping action through centrifugal force. The excessive complexity of the mechanism caused considerable delays in the availability of the engine and the XP-79 was canceled in September, 1944.
XP-79 technical data
Wingspan: 10.90 m (35.7 ft), length: 3.65 m (12 ft), height: 1.05 m (3.44 ft), wing area: 25.82 sq. m (287 sq. ft), max weight: 3,115 kg (6,876 lb.), estimated max speed: 865 km/h (538 miles), ceiling: 12,200 m (40.000 ft).
On January 12, 1943 the Northrop-Maywood aircraft factory was authorized to build three prototypes, but in March the USAAF decided to modify the third airframe (43-52437) as XP-79B powered by two Westinghouse 19 B turbojets.The wingspan of the new model was shortened 61 cm (24 in) and the overall length increased 23 cm (9 in). The wing trailing edge contained elevators,
flaperons and split
decelerons, the foot pedals were connected to air valves, located in ducts on the wing tips that opening the split surfaces to provide braking effect, caused the airplane to turn.
After the accident suffered by the demonstrator N-9M-1 on May 19, 1943, the USAAF ordered the installation of a pair of large vertical stabilizers to prevent flat spin. The XP-79B was destroyed during its first flying test on September 12, 1945. The project was cancelled in January 1946.
XP-79B technical data
Wingspan: 11.58 m (38 ft), length: 4.26 m (14 ft), height: 2.13 m (7 ft), wing area: 25.83 sq. m (287 sq. ft), max weight: 3,933 kg (8,682 lb.), estimated max speed: 880 km/h (547 mph), ceiling: 12,000 m (39,360 ft), range: 480 km (298 miles).
Engines: two Westinghouse 19 B (XJ 30) turbojets with 618 kgp (1,364 lbf) thrust each.
In January 1943, the U.S. Air Material Command ordered the construction of three gliders to prove the concept XP-79. The MX-334/I was used in the aerodynamic tests in the NACA-Langley wind tunnel.
The MX-334/II had skids and flew for the first time on September 4, 1943, towed by a Cadillac. The take-off was quite bumpy, and it was decided to install a detachable trolley. The next flight took place on October 2, towed by one P-38 Lightning.
An Aerojet XCAL R-200 rocket engine, with 90 kgp peak thrust, was installed in June 1944. On July 5, the MX-334/II was towed to 2,500 m (8,200 ft) and successfully made its first powered flight, becoming first rocket plane in America.
The MX-334/III was destroyed at take-off on November 10, 1943. After the accident of the N-9M-1, the other two prototypes received stabilizing vertical surfaces, with support wires.
The MX-334/II changed its designation to MX-324 and got a new (fixed) tricycle landing gear, the main wheels having trousers and the asymmetric nose wheel a spat. The installed engine weighted 194 kg (428 lbs.), including a tank of
Monoethylaniline fuel, a tank of nitric acid oxidant, four pressurized gas bottles, the combustion chamber, and the electric control system.
MX-324 technical data
Wingspan: 10.90 m (35.7 ft), length: 4.34 m (14.2 ft), height: 2.13 m (7 ft), wing area: 23.41 sq. m (260 sq. ft), max weight: 1,656 kg (3,656 lb.), estimated max speed: 480 km/h (298 mph), ceiling: 5,200 m (17,056 ft), range: 480 km (298 miles).
Airframe: wood/plywood/steel tubing.
