Credit
Alan Wilson · CC BY-SA 2.0 · Resized · CC BY-SA 2.0 · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
G 115E · Length
Single source7.79 m (25 ft 7 in)[source]
Kiran IA · Length
Single sourceConfiguration
| Specification | Grob G 115 | HAL HJT-16 Kiran |
|---|---|---|
| Type | Basic trainer[source] | Intermediate jet trainer[source] |
| Manufacturer | Grob Aircraft[source] | Hindustan Aeronautics Limited[source] |
| Status | active[source] | In service[source] |
| Primary users | Royal Air Force Egyptian Air Force Finnish Air Force Royal Navy Army Air Corps (UK)[source] | Indian Air Force Indian Navy |
10.60 m (34 ft 9 in)[source]
Cruise; G 115E · long range cruising speed
Single sourceMaximum; G 115E · Maximum speed
Single source250 km/h (160 mph, 130 kn)[source]
178 km/h (111 mph, 96 kn) (long range cruising speed)[source]
Cruise; Kiran IA · Cruise speed
Single sourceMaximum; Kiran IA · at sea level
Single sourceG 115E · 45% power at FL 80, 45 min reserves
Single source1,150 km (710 mi, 620 nmi) (45% power at FL 80, 45 min reserves)[source]
G 115E · 1 × Lycoming AEIO-360-B1F/B 4-cylinder air-cooled horizontally-opposed piston engine
Single source1 × Lycoming AEIO-360-B1F/B 4-cylinder air-cooled horizontally-opposed piston engine, 130 kW (180 hp)[source]
Kiran IA · 1 × Rolls-Royce Viper 11 turbojet thrust
Single source1 × Rolls-Royce Viper 11 turbojet , 11.12 kN (2,500 lbf) thrust[source]
G 115E · 1,050 ft/min
Single source5.3 m/s (1,050 ft/min)[source]
Kiran IA · Endurance
Single source1 hr 45 min[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Manufactured | 1985–present[source] | 1964 -1989[source] |
|---|
| Introduction date | 1999[source] | 1968[source] |
|---|
| First flight | November 1985[source] | 4 September 1964[source] |
|---|
| Fuel capacity | 143 L (31 imp gal; 38 US gal) usable[source] | 1,137 L (300 US gal; 250 imp gal) internal fuel[source] |
|---|
| Aspect ratio | 8.2:1[source] | 6.03:1[source] |
|---|
| Airfoil | Eppler 696[source] | NACA 23015 at root, NACA 23012 at tip[source] |
|---|
| Propellers | 3-bladed Hoffmann HO-V343K-V/183GY Constant-speed propeller , 1.83 m (6 ft 0 in) diameter[source] | — |
|---|
| Stall speed | 91 km/h (57 mph, 49 kn) (60 degree flap)[source] | 137–145 km/h (85–90 mph, 74–78 kn) flaps extended and landing gear deployed[source] |
|---|
| Never exceed speed | 341 km/h (212 mph, 184 kn)[source] | — |
|---|
| g limits | + 6.0/ - 3.0[source] | — |
|---|
| Country of origin | Deutschland[source]Country of design · Entwurfsland | — |
|---|
| National origin | — | India[source] |
|---|
| Number built | — | 190[source] |
|---|
| Developed into | — | HAL HJT-36 Yashas[source] |
|---|
| Time to altitude | — | 20 min to 9,150 m (30,000 ft)[source] |
|---|