Longitudinal Aerodynamic Characteristics of a Fighter Model With a Close-Coupled Canard at Mach Numbers From 0.40 to 1.20

摘要

An investigation of the longitudinal aerodynamic characteristics of a fighter model with a close-coupled canard mounted above the wing chord plane has been conducted. Model angle of attack was varied from -4° to 15°;canard incidence was varied from -5° to 18°;and selected canard and wing flap deflections were investigated.nThe model could be trimmed by changing canard incidence for lift coefficients up to 0.80 at subsonic free-stream Mach numbers. By using the canard incidence for trim (with canard and wing flaps at 0°), maximum trimmed lift-drag ratios of about 8.8, 7.7, and 4.7 were obtained at free-stream Mach numbers of 0.40, 0.90, and 1.20, respectively. At a lift coefficient of 0.60, model trim angle of attack could be varied over an incremental range (nose-pointing capability) between 3.0° and 3.8°, depending on Mach number, by different combinations of control settings. At high lift coefficients, larger trimmed lift-drag ratios were obtained by using the deflection capability of the canard leading- and trailing-edge flaps before increasing canard incidence angle.