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
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]
Maximum; HTT-40 · Maximum speed
DisputedMaximum; HTT-40 / Max level Speed · Maximum speed
Manufacturer claimG 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]
G 115E · Wing area
Single source12.21 m 2 (131.4 sq ft)[source]
G 115E · 1,050 ft/min
Single source5.3 m/s (1,050 ft/min)[source]
HTT-40 · Endurance
Manufacturer claim3.09 hrs[source]HTT-40
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
Configuration
| Specification | Grob G 115 | HAL HTT-40 |
|---|---|---|
| Type | Basic trainer[source] | Basic training aircraft[source] |
| Manufacturer | Grob Aircraft[source] | Hindustan Aeronautics Limited[source] Hindustan Aeronautics Limited (HAL)[source]HTT-40 |
| Status | active[source] | In service[source] |
| Primary users | Royal Air Force Egyptian Air Force Finnish Air Force Royal Navy Army Air Corps (UK)[source] | — |
| Manufactured | 1985–present[source] | — |
| Introduction date | 1999[source] | 2026 (planned)[source] |
| First flight | November 1985[source] | 31 May 2016[source] |
| Fuel capacity | 143 L (31 imp gal; 38 US gal) usable[source] | 450 kg[source] |
| Aspect ratio | 8.2:1[source] | — |
| Airfoil | Eppler 696[source] | — |
| Propellers | 3-bladed Hoffmann HO-V343K-V/183GY Constant-speed propeller , 1.83 m (6 ft 0 in) diameter[source] | 4-bladed[source] |
| Stall speed | 91 km/h (57 mph, 49 kn) (60 degree flap)[source] | — |
| Never exceed speed | 341 km/h (212 mph, 184 kn)[source] | 450 km/h (279 mph, 243 kn)[source] |
| g limits | + 6.0/ - 3.0[source] | +6/-3[source] |
| Country of origin | Deutschland[source]Country of design · Entwurfsland | — |
| National origin | — | India[source] |
| Designer | — | Aircraft Research and Design Centre[source] |
| Primary user | — | Indian Air Force[source] |
| Number built | — | 3 (excluding 2 prototypes)[source] |
| Developed from | — | HPT-32 Deepak[source] |
| Internal fuel mass | — | 460 kg[source]HTT-40 / Internal fuel mass |
| Take-off Distance | — | 785 meter[source]HTT-40 |
| Landing Distance | — | 987 meter[source]HTT-40 |
| Time to Climb 3 km | — | 7.05 min[source]HTT-40 |
| Engine | — | Honeywell TPE331-12B Turboprop engine[source]HTT-40 |
Gross; HTT-40 / Normal Training Configuration Mass · Gross weight
Single sourceMaximum take-off; HTT-40 / Maximum Take-off Mass · Max takeoff weight
Single source2,800 kg (6,173 lb)[source]
2414 kg[source]HTT-40 / Basic Empty Mass
3040 kg[source]HTT-40 / Maximum Take-off Mass
2960 kg[source]HTT-40 / Normal Training Configuration Mass
Maximum; HTT-40 / Max permissible Speed · @ 6g
Manufacturer claimMaximum; HTT-40 · Maximum speed
Disputed