Accession Number:

AD0601232

Title:

WIND TUNNEL INVESTIGATION OF FAVORABLE INTERFERENCE TO INCREASE LIFT-DRAG RATIOS OF SUPERSONIC AIRCRAFT. PART I - PRESSURE FIELDS AROUND A BODY AND AN INLET.

Personal Author(s):

Corporate Author:

DAVID TAYLOR MODEL BASIN WASHINGTON D C

Report Date:

1964-04-01

Abstract:

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

Pages:

0034

Descriptors:

Communities Of Interest:

File Size:

0.00MB

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