NACA-RM-L55G08

Abstract

INTRODUCTION <br>Recently a wind-tunnel test program was undertaken at the Langley Laboratory of the National Advisory Committee for Aeronautics to obtain aerodynamic data in the transonic and supersonic speed ranges for a series of airplane canopy models mounted on a common fuselage forebody. The primary purpose of this program was to investigate the aerodynamic loads experienced by canopy models that simulate present designs used on high-speed aircraft and to evaluate the effects of such design variables as canopy location, size, and windshield shape. <br>In the present investigation, both pressure-distribution and force data were obtained in the Langley 8-foot transonic tunnel for four different canopies mounted on a fuselage forebody. Presented in this paper are the six-component force data for the canopy-body configurations as well as the forebody alone. Two of the canopies were mounted well forward on the body and had the same shape behind the windshield but one had a "flat" and the.other a "vee" windshield. The two remaining canopies had a smaller maximum cross-sectional area than the first two and both had flat windshields. The two smaller canopies were located at different longitudinal positions on the body. <br>The Mach number range for this investigation was from 0.80 to 1.13 while the angle of attack was varied from 0&#176; to 10&#176; and the angle of side-slip was varied from -8&#176; to 8&#176;.