THK-11

Turkish Aeronautical Association (THK)

Industry	Aviation, Aircraft manufacturing
Founded	1925
Headquarters	Turkey

The THK 11 was a Turkish four-seat monoplane prototype from the 1940s, engineered by Stanisław Rogalski and constructed by the Türk Hava Kurumu (THK - Turkish Aeronautical Association).

Design and development

Featuring a high-wing, twin-boom configuration with a cantilever cabin monoplane layout, the THK-11 was powered by a 135 horsepower (101 kW) de Havilland Gipsy Major piston engine arranged in a pusher propeller setup. The aircraft incorporated a fixed nose-wheel undercarriage and completed its maiden flight in 1947.

Specifications

{{Aircraft specs |ref=Jane's All The World's Aircraft 1951–52, Jane's All The World's Aircraft 1949–50 |prime units?=met |crew=2 |capacity=1 passenger |length m=8.44 |length ft= |length in= |length note= |span m=11.80 |span ft= |span in= |span note= |height m=2.59 |height ft= |height in= |height note= |wing area sqm=18.7 |wing area sqft= |wing area note= |aspect ratio= |airfoil= |empty weight kg=828 |empty weight lb= |empty weight note= |gross weight kg=1150 |gross weight lb= |gross weight note= |max takeoff weight kg= |max takeoff weight lb= |max takeoff weight note= |fuel capacity= | eng1 number=1 | eng1 name=de Havilland Gipsy Major | eng1 type=four-cylinder air-cooled inverted in-line engine | eng1 kw= | eng1 hp=135

| prop blade number=2 | prop name=fixed-pitch pusher propeller | prop dia m= | prop dia ft= | prop dia in= | prop dia note=

|max speed kmh=201 |max speed mph= |max speed kts= |max speed note= | cruise speed kmh=164 | cruise speed mph= | cruise speed kts= | cruise speed note=

• Landing speed: 80 km/h (50 mph; 43 kn)

| stall speed kmh= | stall speed mph= | stall speed kts= | stall speed note= | never exceed speed kmh= | never exceed speed mph= | never exceed speed kts= | never exceed speed note= | range km=800 | range miles= | range nmi= | range note=in calm conditions | endurance=

| ceiling m=3500 | ceiling ft= | ceiling note=

| g limits=

| roll rate=

| climb rate ms=

| climb rate ftmin=690 | climb rate note=

| time to altitude=

| wing loading kg/m2=61.5 | wing loading lb/sqft=

| wing loading note=

| fuel consumption kg/km=

| fuel consumption lb/mi=

| power/mass=11.4 kg/kW (18.7 lb/hp)

|}