Credit
Alan Wilson · CC BY-SA 2.0 · Resized · CC BY-SA 2.0 · Source ↗ · Modified
FORCETALLY
Loading the evidence…
Preparing your view.
Preparing your view.
At a glance
Measured figures
G 115E · Length
Single source7.79 m (25 ft 7 in)[source]
UTVA 75A21 · Length
Single sourceConfiguration
| Specification | Grob G 115 | UTVA 75 |
|---|---|---|
| Type | Basic trainer[source] | Military and civilian trainer aircraft[source] |
| Manufacturer | Grob Aircraft[source] | UTVA[source] |
| Status | active[source] | Active[source] |
| Primary users | Royal Air Force Egyptian Air Force Finnish Air Force Royal Navy Army Air Corps (UK)[source] | — |
| Manufactured |
7.11 m (23 ft 4 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; UTVA 75A21 · Cruise speed
Single sourceMaximum; UTVA 75A21 · Maximum speed
Single sourceG 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]
UTVA 75A21 · 1 × Lycoming IO-360-B1F 4-cyl. air-cooled horizontally-opposed piston engine
Single source1 × Lycoming IO-360-B1F 4-cyl. air-cooled horizontally-opposed piston engine, 134 kW (180 hp)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
1985–present[source] |
| — |
| Introduction date | 1999[source] | 1978[source] |
|---|
| First flight | November 1985[source] | 19 May 1976[source] |
|---|
| Fuel capacity | 143 L (31 imp gal; 38 US gal) usable[source] | standard:160 L (42 US gal; 35 imp gal): with drop tanks 360 L (95 US gal; 79 imp gal)[source] |
|---|
| Aspect ratio | 8.2:1[source] | 6.5[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] | 2-bladed Hartzell HC-C2YK-1BF/F7666A variable-pitch metal propeller[source] |
|---|
| Stall speed | 91 km/h (57 mph, 49 kn) (60 degree flap)[source] | 95 km/h (59 mph, 51 kn) flaps up at idle[source] |
|---|
| Never exceed speed | 341 km/h (212 mph, 184 kn)[source] | 270 km/h (168 mph, 146 kn)[source] |
|---|
| g limits | + 6.0/ - 3.0[source] | +4.4 -2.2[source] |
|---|
| Country of origin | Deutschland[source]Country of design · Entwurfsland | — |
|---|
| National origin | — | Yugoslavia[source] |
|---|
| Primary user | — | Serbia Air Force[source] |
|---|
| Capacity | — | 210 kg (460 lb) max[source] |
|---|
| Takeoff distance to 50 ft (15 m) | — | 501 m grass at Sea Level[source] |
|---|
| Landing distance from 50 ft (15 m) | — | 450 m grass at Sea Level[source] |
|---|
| Hardpoints | — | 2 with a capacity of 150 kg (330 lb) each, with provisions to carry combinations of:[source] |
|---|
| Rockets | — | 2 × RL 128-02 128 mm (HVAR-5), or 2 × 57 millimetres (2.2 in) rocket launchers with 12 rockets[source] |
|---|
| Bombs | — | 2 × 120 kg bombs, or 4 × 50 kg bombs[source] |
|---|
| Other | — | 2 × MAC-AA-52 container with 7.62 mm , or 2 × cargo container 100 kg capacity, or 2 × drop tanks[source] |
|---|
| standard | — | (model 75) KING KR85 ADF and KING KY 195B[source] |
|---|
| optional | — | (model 75A catalog only) KING KR87 ADF, RNAV KING KNS81 VOR/LOC: KING KN 53, KING KY 197 Indicators: HSI KING KI 525A, and RMI KING KI 229, DME:KING KN 62A, Transponder: KING KT 79, Audio panel: KING KMA 24[source] |
|---|