Accession Number:

AD0261507

Title:

PRESSURE DISTRIBUTION TEST OF SHARP LEADING-EDGE WING AND WING-BODY COMBINATIONS AT MACH 21

Descriptive Note:

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN

Personal Author(s):

Report Date:

1961-08-01

Pagination or Media Count:

27.0

Abstract:

Pressure distribution tests were made on a delta wing model and two wing-body combinations, all with sharp leading edges, in tunnel Hotshot 2 at a Mach number of 21 and a Reynolds number per foot of 400,000. Angle of attack ranged from -5 to 20 deg. Typical spanwise pressure distributions on the flat lower surface of model W4 are shown. It is observed that the pressure increases near the leading edge. The effect of adding the body to model W4 to obtain model W4B1 increases the pressure considerably over the entire lower surface. The spanwise pressure distribution of model W-B1 on the upper and lower surfaces is also shown. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE