Author: M. B. GuyettPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Low Speed Wind Tunnel Tests on the de Havilland Sea Venom with a Part-span Sharp Wing-leading-edge Extension
Author: M. B. GuyettLow Speed Wind Tunnel Tests on the de Havilland Sea Venom with Blowing Over the Flaps
Author: S.F.J. ButlerCurrent Papers
Author: Preliminary Note on Wind Tunnel Tests on the De Havilland Sea Venom with Blowing Over the Flaps
Author: S. F. J. ButlerLow-speed Wind-tunnel Tests on an Unswept Wing of Aspect Ratio 7 with Plain Part-span Trailing-edge Flaps
Author: J. McKieLow-speed Wind-tunnel Tests on a Series of Uncambered Slender Pointed Wings with Sharp Edges
Author: D. H. PeckhamPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 83
Book Description
Low Speed Wind Tunnel Tests on a Fully Tapered Wing with 81 Degrees Leading Edge Sweep and a 6% Thick RAE 101 Section
Author: D. A. KirbyWind Tunnel Investigation at Low Speed of a Twisted and Cambered Wing Swept Back 63 Degrees with Vortex Generators and Fences
Author: James A. WeilbergLtv Low Speed Wind Tunnel Test Number 190, Follow-on Test of High Mass Rate Vectored Propulsion Flow Model
Author: J. K. DavidsonPublisher:
ISBN:
Category :
Languages : en
Pages : 200
Book Description
The wind tunnel data resulting from a low speed wind tunnel follow-on test of a semi-span model of a close support, VTOL aircraft is presented. The model features an integrated propulsion/lifting surface system as well as vertical and horizontal tails located on an aft, wing tip extension. The propulsion system exhaust flow, which is simulated with cold air, exhausts over the wing trailing edge flap (flap jet) and out of the lower surface of the wing (wing box jet). The exhaust flows can be independently vectored through 90 degrees with respect to the wing chord plane. The test data are presented in the form of lift and rolling moment coefficients as functions of angle of attack, and drag and pitch moment coefficients as functions of lift coefficient. The coefficient data are given with and without the direct thrust contribution included. The static thrust data are given in the form of lift, drag, pitching moment and rolling moment as functions of angle of attack. Test data with and without ground board effects are presented. (Author).
Author: S. F. J. Butler