Investigation of trailing-edge-flap, spanwise-blowing concepts on an advanced fighter configuration
- Author:
- Banks, D. W.
- Published:
- Mar 1, 1984.
- Physical Description:
- 1 electronic document
- Additional Creators:
- Quinto, P. F.
Paulson, J. W., Jr. - Access Online:
- hdl.handle.net
- Restrictions on Access:
- Unclassified, Unlimited, Publicly available.
- Summary:
- 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.
- Collection:
- NASA Technical Reports Server (NTRS) Collection.
- Note:
- Document ID: 19840010096.
Accession ID: 84N18164.
NAS 1.60:2250.
L-15627.
NASA-TP-2250. - Terms of Use and Reproduction:
- No Copyright.
- Access Online:
- hdl.handle.net
View MARC record | catkey: 15708740