WIND TUNNEL INVESTIGATION OF FAVORABLE INTERFERENCE TO INCREASE LIFT-DRAG RATIOS OF SUPERSONIC AIRCRAFT. PART I - PRESSURE FIELDS AROUND A BODY AND AN INLET.
DAVID TAYLOR MODEL BASIN WASHINGTON D C
Pagination or Media Count:
Wind-Tunnel tests at a Mach number of 2.87 were to measure the intensity and spatial distribution of low-pressure fields that radiate back from an indented side portion of a body and the high-pressure fields that radiate from the external wedge sides of an engine air inlet. The measured pressure distributions were integrated over a proposed thin flat-plate wing proposed for separating the body and inlet fields. The resulting favorable increase in normal-force coefficient was as much as 0.035 at zero angle of attack and corresponds to about 15 percent of the cruise lift required for an attack aircraft. Author