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North American YF-93

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.



Original designation for a re-engine variant of the F-86A, two built.


Two prototype F-86Cs redesignated,


Production variant, order for 118 cancelled.





44 ft 1 in (13.44 m)


38 ft 9 in (11.81 m)


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)


1 × Pratt & Whitney J48-P-6 turbojet,

6,000 lbf (27 kN) thrust dry,

8,750 lbf (38.9 kN) with afterburner


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)


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)



6× 20mm M24 cannon (proposed, not fitted to the prototypes).



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