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Investigation of trailing-edge-flap, spanwise-blowing concepts on an advanced fighter configuration (1984)

Banks, D. W. ; Quinto, P. F. ; Paulson, J. W., Jr.

In: CASI

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Publication Date: 2019-06-28

Description: The aerodynamic effects of spanwise blowing on the trailing edge flap of an advanced fighter aircraft configuration were determined in the 4 by 7 Meter Tunnel. A series of tests were conducted with variations in spanwise-blowing vector angle, nozzle exit area, nozzle location, thrust coefficient, and flap deflection in order to determine a superior configuration for both an underwing cascade concept and an overwing port concept. This screening phase of the testing was conducted at a nominal approach angle of attack from 12 deg to 16 deg; and then the superior configurations were tested over a more complete angle of attack range from 0 deg to 20 deg at tunnel free stream dynamic pressures from 20 to 40 lbf/sq ft at thrust coefficients from 0 to 2.

Keywords: AERODYNAMICS

Type: NASA-TP-2250 , L-15627 , NAS 1.60:2250

Format: application/pdf

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