The North American YF-93 was an American fighter development of the F-86 Sabre that emerged as a radically different variant that received its own designation.
Two were built and flown before the project was eventually cancelled.
In 1947, North American Aviation began a design study, NA-157, to create a true “penetration fighter” to meet the requirements of a long-range version of its F-86A Sabre.
In order to accommodate more fuel, a much larger F-86A was envisioned, eventually able to carry 1,961 US gallons (7,420 l), both internally and with two 200-US-gallon (760 l) underwing drop tanks.
The new variant possessed a theoretical unrefuelled range of over 2,000 nmi (2,300 mi; 3,700 km), twice that of the standard production F-86A.
The resultant fighter originally designated the F-86C was intended to compete with the XF-88 Voodoo and Lockheed XF-90 to fulfill the USAF’s Penetration Fighter requirement for a bomber escort.
The F-86C was much larger and heavier, weighing in at 10,640 lb (4,830 kg) more than its antecedent.
The increased weight and girth necessitated a dual-wheel main landing gear, increased wing area and a more powerful engine, the Pratt & Whitney J48 rated at 6,250 lbf (27.8 kN) static thrust and 8,750 lbf (38.9 kN) thrust available in afterburner.
With the SCR-720 search radar and six 20 mm (.79 in) cannon mounted in the nose where the air intake was on the F-86A, the engineers designed a novel set of flush-mounted NACA inlets.
In December 1947, the Air Force ordered two prototype NA-157s and, considering the many changes to the F-86, redesignated it YF-93A.
Both prototypes were built with NACA inlet ducts; the first, (48-317), was later retrofitted with more conventional intakes.
Six months later, the initial contract was followed up with an order for 118 F-93A-NAs.
In 1949, the production order was abruptly cancelled as priorities had shifted dramatically following the testing of the ground-breaking Boeing B-47 which reputedly would not need an escort due to its high-speed capabilities.
With the prototype YF-93As just coming off the production line, the USAF took over the project.
Variants
F-86C
Original designation for a re-engine variant of the F-86A, two built.
YF-93A
Two prototype F-86Cs redesignated,
F-93A
Production variant, order for 118 cancelled.
Specifications
Crew
1
Length
44 ft 1 in (13.44 m)
Wingspan
38 ft 9 in (11.81 m)
Height
15 ft 8 in (4.78 m)
Wing area
306 sq ft (28.4 m2)
Empty weight
14,035 lb (6,366 kg)
Gross weight
21,610 lb (9,802 kg)
Max take-off weight
26,516 lb (12,027 kg)
Powerplant
1 × Pratt & Whitney J48-P-6 turbojet,
6,000 lbf (27 kN) thrust dry,
8,750 lbf (38.9 kN) with afterburner
Performance
Maximum speed
708 mph (1,139 km/h, 615 kn) at sea level,
622 mph (1,001 km/h; 541 kn) at 35,000 ft (11,000 m)
Cruise speed
534 mph (859 km/h, 464 kn)
Range
1,967 mi (3,166 km, 1,709 nmi)
Service ceiling
46,800 ft (14,300 m)
Rate of climb
11,960 ft/min (60.8 m/s)
Armament
Guns
6× 20mm M24 cannon (proposed, not fitted to the prototypes).
