Fighter Technology Demonstrator Precursor Analysis and Test. Volume II. An Experimental Investigation of the Aerodynamic Characteristics of a Fighter Technology Demonstrator Jet Flap Development Model at Low Subsonic Mach Number.
Final rept. May-Oct 73,
ROCKWELL INTERNATIONAL CORP LOS ANGELES CALIF LOS ANGELES AIRCRAFT DIV
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A subsonic wind tunnel test of a small-scale fighter technology demonstrator development model was conducted to obtain data instructive in refining and developing the configuration. Tests were performed at mach 0.23 through high angles of attack and at angles of sideslip for various geometric alterations to the configuration to evaluate their impact on the design aerodynamics. Flow surveys were conducted to evaluate flow fields at potential inlet locations. Additional tests were conducted, with a secondary air source providing thrust, for a jet flap arrangement at the wing trailing edge. This jet flap configuration incorporates the features of an aerodynamic flap and jet flap in that the turning action of the conventional mechanical flap also directs the jet efflux. Deflection angles of the jet were 0, 10, 20, and 30 degrees for two flap spans. Modified author abstract
- Attack and Fighter Aircraft