Grumman F-9 Cougar

The Grumman F9F/F-9 Cougar was a carrier-based fighter aircraft for the United States Navy and United States Marine Corps.

Variants

XF9F-6

Prototypes built from the F9F-5 Panther, featuring swept-wing design.

F9F-6

Initial production version; redesignated F-9F in 1962.

F9F-6P

Photo-reconnaissance versions; redesignated RF-9J in 1962.

F9F-6PD

Drone director aircraft, converted from F9F-6Ps; redesignated DF-9F in 1962.

F9F-6D

Drone director aircraft, converted from F9F-6s; redesignated DF-9F in 1962.

F9F-6K

Unmanned drone for combat training, converted from F9F-6s; redesignated QF-9F in 1962.

F9F-6K2

An improved version of the F9F-6K target drone; redesignated QF-9G in 1962.

F9F-7

Built with the Allison J33 engine; most were converted to take J48s; redesignated F-9H in 1962.

F9F-8

Longer centre fuselage, strengthened canopy, redesigned wing, increased fuel capacity, and the ability to carry AIM-9 Sidewinder missiles; redesignated F-9J in 1962.

YF9F-8B

Prototype for a single-seat attack-fighter aircraft converted from a F9F-8; later redesignated YAF-9J.

F9F-8B

F9F-8s converted into single-seat attack-fighters; later redesignated AF-9J.

F9F-8P

Photo-reconnaissance versions built from F9F-8s; later redesignated RF-9F.

YF9F-8T

One F9F-8 aircraft converted into a prototype for the F9F-8T training aircraft; later redesignated YTF-9J.

F9F-8T

Two-seat trainers built from F9F-8s; redesignated TF-9J in 1962.

NTF-9J

Two TF-9Js used for special test duties.

YF9F-9

Original designation of the YF11F-1 Tiger prototypes.

First flight was on 30 July 1954; redesignated in April 1955.

Specifications

Crew

1

Length

40 ft 11 in (12.47 m)

Wingspan

34 ft 6 in (10.52 m)

Width

14 ft 2 in (4.32 m) folded (tail plane span)

Height

12 ft 3.5 in (3.747 m)

Height folded

15 ft 10 in (4.8 m) (wing-tips

Wing area

300 sq ft (28 m2)

Aspect ratio

4

Airfoil

NACA 64A010

Empty weight

11,483 lb (5,209 kg)

Empty equipped

12,090 lb (5,484 kg)

Gross weight

15,800 lb (7,167 kg)

Combat weight

16,244 lb (7,368 kg)

Max take-off weight

21,000 lb (9,525 kg) on land

20,000 lb (9,072 kg) from catapult

Maximum landing weight

16,000 lb (7,257 kg) on land

14,000 lb (6,350 kg) arrested landing

Fuel capacity

763 US gal (635 imp gal; 2,890 l) in two fuselage tanks

&

156 US gal (130 imp gal; 590 l) in four wing leading edge tanks; total 919 US gal (765 imp gal; 3,480 l)

Powerplant

1 × Pratt & Whitney J48-P-8 centrifugal-flow turbojet engine, 7,250 lbf (32.2 kN) thrust at 11,000 rpm for take-off / Military power at sea level

5,600 lbf (24.91 kN) at 10,450 rpm maximum continuous at sea level

Performance

Maximum speed

654 mph (1,053 km/h, 568 kn) at sea level at 18,450 lb (8,369 kg) TOW

Cruise speed

541 mph (871 km/h, 470 kn) at 41,200–45,000 ft (12,558–13,716 m)

Stall speed

128 mph (206 km/h, 111 kn) at 18,450 lb (8,369 kg) TOW power off

107 mph (93 kn; 172 km/h) at 15,157 lb (6,875 kg) with approach power

Combat range

293 mi (472 km, 255 nmi) with 1 hour 24 minutes mission time

Service ceiling

44,500 ft (13,600 m)

G limits

+7.5 at 15,800 lb (7,167 kg); +5.5 at MTOW

Rate of climb

6,750 ft/min (34.3 m/s) at sea level at 18,450 lb (8,369 kg)

TOW

Time to altitude

20,000 ft (6,096 m) in 4 minutes at 18,450 lb (8,369 kg)

TOW

30,000 ft (9,144 m) in 6 minutes 48 seconds at 18,450 lb (8,369 kg) TOW

Wing loading

61.5 lb/sq ft (300 kg/m2) at 18,450 lb (8,369 kg) TOW

Take-off run

2,100 ft (640 m) at 18,450 lb (8,369 kg)

TOW in nil wind

1,360 ft (415 m) at 18,450 lb (8,369 kg)

TOW in 29 mph (25 kn; 47 km/h) wind

Armament

Guns

4 × 20 mm (0.79 in) AN/M3 cannon, 190 rounds per gun

Rockets

6 × 5 in (127 mm) rockets

Bombs

2 × 1,000 lb (454 kg) bombs on inboard pylons

plus

2 x 500 lb (227 kg) bombs on outer pylons

Avionics

Radar ranging 

AN/APG-30.

 

 

 

 

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