Grob G 115 vs Kawasaki T-4: Specs Compared

Grob G 115 — licensed reference photograph

ATrainer aircraft

Grob G 115

Basic trainer

Credit

Alan Wilson · CC BY-SA 2.0 · Resized · CC BY-SA 2.0 · Source ↗ · Modified

Kawasaki T-4 — licensed reference photograph

BTrainer aircraft

Kawasaki T-4

Intermediate trainer aircraft

Credit

Jerry Gunner · CC BY-SA 4.0 · Resized · CC BY-SA 4.0 · Source ↗ · Modified

First system

Second system

At a glance

Side by side

Length comparisonOne shared metre scale

Grob G 115G 115E · Length

7.79 m

Length source ↗

Kawasaki T-4T-4 · Length

13 m

Length source ↗

Lengths retain their source configuration and measurement scope.

Measured figures

Head to head

19 of 30 rows sourced on both sides

7.79mG 115E · Length

13mT-4 · Length

LengthScopes differ

All recorded figures & sources

7.79 m

G 115E · Length

Single source

7.79 m (25 ft 7 in)^[source]

13 m

T-4 · Length

Single source

13.00 m (42 ft 8 in)^[source]

10mG 115E · Wingspan

9.94mT-4 · Wingspan

WingspanScopes differ

All recorded figures & sources

10 m

G 115E · Wingspan

Single source

10.00 m (32 ft 10 in)^[source]

9.94 m

T-4 · Wingspan

Single source

9.94 m (32 ft 7 in)^[source]

2.82mG 115E · Height

4.6mT-4 · Height

HeightScopes differ

All recorded figures & sources

2.82 m

G 115E · Height

Single source

2.82 m (9 ft 3 in)^[source]

4.6 m

T-4 · Height

Single source

4.60 m (15 ft 1 in)^[source]

990kg

7.5t

MassScopes differ

All recorded figures & sources

670 kg

Empty; G 115E · Empty weight

Single source

990 kg

Maximum take-off; G 115E · Max takeoff weight

Single source

670 kg (1,477 lb)^[source]

990 kg (2,183 lb)^[source]

3,700 kg

Empty; T-4 · Empty weight

Single source

7,500 kg

Maximum take-off; T-4 · Max takeoff weight

Single source

2G 115E · Crew

2T-4 · Crew

CrewScopes differ

All recorded figures & sources

2 people

G 115E · Crew

Single source

2^[source]

2 people

T-4 · Crew

Single source

2^[source]

250km/hMaximum; G 115E · Maximum speed

1,038km/hMaximum; T-4 · at sea level

SpeedScopes differ

All recorded figures & sources

178 km/h

Cruise; G 115E · long range cruising speed

Single source

250 km/h

Maximum; G 115E · Maximum speed

Single source

250 km/h (160 mph, 130 kn)^[source]

178 km/h (111 mph, 96 kn) (long range cruising speed)^[source]

1,038 km/h

Maximum; T-4 · at sea level

Single source

1,038 km/h (645 mph, 560 kn) at sea level^[source]

1,150km

1,668km

RangeScopes differ

All recorded figures & sources

1,150 km

G 115E · 45% power at FL 80, 45 min reserves

Single source

1,150 km (710 mi, 620 nmi) (45% power at FL 80, 45 min reserves)^[source]

1,668 km

T-4 · with two 450 L (99 imp gal; 120 US gal)

Single source

1,668 km (1,036 mi, 901 nmi) with two 450 L (99 imp gal; 120 US gal)^[source]

130kW

—

Power

All recorded figures & sources

130 kW

G 115E · 1 × Lycoming AEIO-360-B1F/B 4-cylinder air-cooled horizontally-opposed piston engine

Single source

1 × Lycoming AEIO-360-B1F/B 4-cylinder air-cooled horizontally-opposed piston engine, 130 kW (180 hp)^[source]

—

16.3kN

Thrust

All recorded figures & sources

16.32 kN

T-4 · 2 × Ishikawajima-Harima F3 -IHI-30 turbofans thrust each

Single source

2 × Ishikawajima-Harima F3 -IHI-30 turbofans , 16.32 kN (3,670 lbf) thrust each^[source]

12.2m²G 115E · Wing area

21m²T-4 · Wing area

Wing areaScopes differ

All recorded figures & sources

12.21 m²

G 115E · Wing area

Single source

12.21 m 2 (131.4 sq ft)^[source]

21 m²

T-4 · Wing area

Single source

21.00 m 2 (226.0 sq ft)^[source]

6,095mG 115E · Service ceiling

15,240mT-4 · Service ceiling

Service ceilingScopes differ

All recorded figures & sources

6,095 m

G 115E · Service ceiling

Single source

6,095 m (20,000 ft)^[source]

15,240 m

T-4 · Service ceiling

Single source

15,240 m (50,000 ft)^[source]

5.3m/sG 115E · 1,050 ft/min

51m/sT-4 · 10,000 ft/min

Rate of climbScopes differ

All recorded figures & sources

5.3 m/s

G 115E · 1,050 ft/min

Single source

5.3 m/s (1,050 ft/min)^[source]

51 m/s

T-4 · 10,000 ft/min

Single source

51 m/s (10,000 ft/min)^[source]

Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.

Configuration

Details

Grob G 115 and Kawasaki T-4 configuration
Specification	Grob G 115	Kawasaki T-4
Type	Basic trainer^[source]	Intermediate trainer aircraft^[source]
Manufacturer	Grob Aircraft^[source]	Kawasaki^[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	1985–present^[source]	208+^[source]
Introduction date	1999^[source]	1988^[source]
First flight	November 1985^[source]	29 July 1985^[source]
Fuel capacity	143 L (31 imp gal; 38 US gal) usable^[source]	2,241 L (493 imp gal; 592 US gal) internal fuel^[source]
Aspect ratio	8.2:1^[source]	4.7:1^[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]	—
Stall speed	91 km/h (57 mph, 49 kn) (60 degree flap)^[source]	167 km/h (104 mph, 90 kn)^[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	—	Japan^[source]
Primary user	—	Japan Air Self-Defense Force^[source]
Hardpoints	—	5 (4 underwing and 1 under fuselage) for drop tanks, practice bombs and target towing equipment^[source]

FORCETALLY

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Grob G 115

Kawasaki T-4

Type

Basic trainer^[source]

Intermediate trainer aircraft^[source]

Manufacturer

Grob Aircraft^[source]

Kawasaki^[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

1985–present^[source]

208+^[source]

Introduction date

1999^[source]

1988^[source]

First flight

November 1985^[source]

29 July 1985^[source]

Fuel capacity

143 L (31 imp gal; 38 US gal) usable^[source]

2,241 L (493 imp gal; 592 US gal) internal fuel^[source]

Aspect ratio

8.2:1^[source]

4.7:1^[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]

—

Stall speed

91 km/h (57 mph, 49 kn) (60 degree flap)^[source]

167 km/h (104 mph, 90 kn)^[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

—

Japan^[source]

Primary user

—

Japan Air Self-Defense Force^[source]

Hardpoints

—

5 (4 underwing and 1 under fuselage) for drop tanks, practice bombs and target towing equipment^[source]