Possibility of increasing lift coefficient of aircraft to almost twice its value, without deflection of flaps, by means of continuously distributed boundary layer suction in region of leading edge of wing, is illustrated by flight experiments with RW 3a aircraft; results are given of wind tunnel experiments with original wing of RW 3a investigating essentially losses in pressure due to flow permeating porous skin of wing.
Flight tests on aircraft Model RW 3a having boundary layer suction to increase maximum lift
Flugversuche am Baumuster RW 3a mit Grenzschichtabsaugung zur Steigerung des Hoechstauftriebs
Zeitschrift fuer Flugwissenschaften ; 11 , n 4
1963
8 pages
Aufsatz (Zeitschrift)
Deutsch
© Metadata Copyright Elsevier B. V. All rights reserved.
Ship model tests with boundary layer suction
TIBKAT | 1986
|Distributed suction boundary layer control for high lift
Engineering Index Backfile | 1968
|Distributed Suction Boundary Layer Control for High Lift
SAE Technical Papers | 1968
|Flight experiments on suction for high lift
AIAA | 1965
|