Wind tunnel tests on LCA 6.02 configuration

Tests were conducted in the NAL 1.2m trisonic wind tunnel on a 1/20th scale model of the LCA Stage 6.02 configuration. The tests were carried out in a Mach number range of 0.5 to 1.6 and over an angle of attack range which varied from -5 deg to +28 deg at M = 0.5 to -5 deg to +12 deg at M = 1.6. The test Reynolds number (based on wing mean aerodynamic chord) varied between 4.8 to 10.28 millions depending on the Mach number. The tests Included : (i) determination of the longitudinal characteristics of the configuration and (ii) determination of longitudinal, lateral and directional control powers