SD-260 Detail Specification for Model XF5F-1 Airplane, May 5, 1938

Page 1. As a landplane, it shall take off from the deck of an aircraft carrier with or without the aid of a catapult and land on the carrier deck in an arresting gear or ordinary landing field.

Par. 101. The following characteristics are considered reasonable for this airplane and shall equalled or bettered.

The gross weights are estimated to be as follows.

Fighter (163 gallons)

8253

Bomber (200# A.A. bombs, 163 gals.)

8493

Fighter (255 gals. maximum)

8942

Par. 104a. The useful load as a fighter shall be as 1789 pounds.

Armament consisting of fixed gun installation (2-.50 cal. and 2-.30 cal 385.8#.

104b. The useful load as a bomber with 200 pounds anti-aircraft bombs and 163 gals. of fuel shall be 2029 pounds.

104c. The useful load as a fighter with maximum ammunition and with 255 gal. fuel (max) and 18 gal oil (max) shall be 2478 pounds.

105a. The weight empty as a carrier land plane is estimated to be 6464 pounds.

107a. The horsepower for 2 Pratt and Whitney R-1535-2 engines is estimated to be 1500 from sea level to 17,500 feet altitude at 2550 RPM with 3-blade propeller. For take-off the 2 engines are rated at 1650 HP at 2630 RPM.

111a The unit loadings shall be as follows.


Wing Load

Lbs/sq.ft.(278)

Power Load

Lbs/BHP (1500)

Fighter (163 gals.)

29.7

5.52

Bomber (163 gallon and A.A. Bombs)

30.4

5.65

Fighter (255 gallons maximum)

32.2

5.97

112a. The airfoil section shall be NACA 23009-15 tapered.

113a. The performance is estimated to be:


Fighter 163 Gal.

Bomber 163 gal.

Fighter 255 gal.

Gross weight.

8253

8493

8942

Full Speed MPH at 17,500 ft.

350

354

340

Full Speed MPH at sea level

290

286

283

Stalling speed with power.

70

71

73

Stalling speed without power

76

77

79

Climb to 5000 ft. (minutes)

1.33

1.39

1.50

Climb to 15,000 ft. (minutes)

4.03

4.23

4.55

Service ceiling (ft.)

31,500

30,000

26,000

End. at V.max.

0.93

0.93

1.46

Endurance at 90% V Max. (315 MPH)

1.70

1.68

2.55

Endurance at 75% V. Max. (263 MPH)

2.58

2.54

3.80

Endurance at 60% V. Max. (210 MPH)

3.98

3.9

5.6

Take-off in calm (feet)

600

675

780

Take-off in 15 knot wind.

345

390

450

Take-off in 25 knot wind.

225

255

290

Range at economical speed.

1,000

1,000

1,600

The above performance is based on 1500 HP at 17,500 ft and at sea level at 2550 RPF with 3-blade propeller. For take-off the 2 engines are rated at 1650 HP at 2630 RPM. The above performance is calculated with all external armament and radio equipment in place for each condition of loading.

116a.

Span (wings extended)

40'


Span (wings folded)

20'


Length Overall

27'


Mean aerodynamic chord.

88.8"

503a The two engines shall be Pratt and Whitney Model R-1535-2 2 stage geared 3 to 2. and rated at 1500 HP at 2550 RPM at sea level and 17500 ft. altitude.

551a. Two three-blade constant speed hydromatic propellers with constant speed governor units shall be furnished by the government. he blades shall be Hamilton Standard Design No. 6129 diameter 9' 6".

552 a. The propellors shall be arranged to turn in opposite directions.

996a. The armament installation shall consist of the following main items.

2-.30 cal. Browning aircraft machine gun installations with 1000 rounds of ammunition in the fuselage.

2-.50 cal. Browning aircraft machine gun installations with 400 rounds of amm. Or two 23 MM Madsen machine guns with 200 rounds of ammunition in the fuselage.