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The F-95A was an early designation for the F-86D. The prototype aircraft (S/N 50-577 & 50-578) were originally designated YF-86D, changed to YF-95A and finally re-designated YF-86D. Similarly, the production aircraft were designated F-95A, but changed to F-86D before production began.

The information on this page is from documents dated 28 Feb. 1950 when the aircraft was being developed as the F-95A.

Mission and Description
The tactical mission of the F-95A is the interception and destruction of hostile aircraft in flight during day or night and in all types of weather.

Special features in the general arrangement of the airplane are swept-back wing and tail and an under slung engine air inlet duct fairing into the fuselage. All fuel for the intercept mission is carried internally, but there are provisions for external wing tanks.

The airplane control systems provide for: hydraulic power-operated irreversible controls, with artificial feel for the all-movable horizontal tail and ailerons, and a conventional pilot-operated rudder.

The cockpit is provided with equipment for 5.0 psi differential pressurization, heating and cooling and a jettisonable hinged-type canopy; also an ejection-type seat, and anti-G suit controls, and an F-5 automatic pilot.

An isobarically controlled pressurized fuel system is installed. Fuel cell and fuel cell bay purging is accomplished by engine exhaust gas.

High lift devices consist of electrically operated single-slotted wing flaps and aerodynamically actuated wing leading edge slots.

Speed brakes are located on the aft portion of the fuselage and are hydraulically operated.

Click on Picture to enlarge

North American            F-95A drawings

Side view cutaway - showing basic component placement

3/4 front view cutaway - showing fuel cell placement and 2 gallon oil tank

SPECIFICATIONS (F-95A)
Span: 37.1 ft.

Incidence (root): +1 degree

Incidence (tip): -1 degree

Dihedral: 3 degrees

Sweepback: 35 degrees

Wing area: 287.9 sq. ft.

Aspect ratio: 4.79
Length: 41.8 ft.
Height: 15.0 ft.
Tread: 8.3 ft. (distance between main landing gear)
Weights:

Empty: 12,470 lbs. (Actual)

Basic: 12,521 lbs. (Actual)

Design: 13,395 lbs.

Combat: 14,900 lbs. (for basic mission)

Max. Take-off: 18,483 lbs. (limited by strength)

Max. Landing: 18,483 lbs. (limited by strength)
Armament: Twenty-four 2.75 in. Folding Fin Aerial Rockets (FFAR) in retractable fuselage launcher.

Rocket sight: Hughes electronic fire computer
Engine: General Electric J47-GE-17 axial flow turbojet rated at:

Max. Power: 7,630 lbs. thrust at 7,950 RPM with afterburner

Military Power: 5,670 lbs. thrust at 7,950 RPM

Normal Power: 5,300 lbs. thrust at 7,630 RPM
Crew: One
Electronics:

VHF Command: AN/ARC-3

Search Radar: AN/APG-33

Identification Radar: AN/APX-6

Glide Path: AN/ARN-5A

Localizer: RC-103A

Marker Beacon: AN/ARN-12

Radio Compass: AN/ARN-6

PERFORMANCE
Maximum speed: 614 knots at sea level, max. power
Combat speed: 539 knots at 40,000 ft., max. power
Combat range: 537 nautical miles at 468 knots average in 1.21 hours
Combat radius: 147 nautical miles at 483 knots average in .89 hours (Note: the combat allowance for the F-95A has been limited to 5 minutes instead of 20 minutes to afford practical combat radius.)
Rate of climb: 18,150 fpm. (max.) at sea level, combat weight, max. power
Service ceiling: 54,000 ft., combat weight, max. power
Take-off ground run:

1,563 ft. no assist

3,030 ft. to clear a 50 ft. obstacle
Stall speed: 108 knots
Time to climb: 5.9 minutes from standstill to 40,000 ft., max. power, take-off weight
Fuel load: 848 gallons of AN-F-58 JP-3; 233 gals in 3 wing tanks, 375 gals. in 2 fuselage tanks, and 240 gals. in two wing drop tanks.
Oil load: 2 gallons of Spec. AN-0-9 Grade 1010

 

This aircraft information is from the USAF Museum Archives.

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