Abstract:
Results are given of pressure measurements on awing
of gross aspect ratio approximately 2/3 mounted on a cylindrical
body with an ogival nose, made at a Mach number of 2.00 in the
9in, x 9in, supersonic -wind tunnel at the College of Aeronautics.
The wing section was a single wedge having a 6° total nose angle.
The ranges of body incidence and roll in these tests were from
0° to 30°, and 0°, 30°, 600 and 90° respectively. The normal
force, lift, drag and side force coefficients, and rolling and
pitching moments were obtained from the pressure measurements.
