North American F-95A
     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 redesignated 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 des-
 truction 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 underslung 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 hydraulicaly operated.
 TYPE                   Number built/Converted
 YF-95A                         2
 F-95A                          0
 Remarks:  was YF-86D; to YF-95A; became YF-86D
           2,504 built as F-86D
 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
 Identication 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
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--- DB 1.39/004487
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