HEAT-TRANSFER MEASUREMENTS AT A MACH NUMBER OF 4.95 ON TWO 60° SWEPT DELTA WINGS WITH BLUNT LEADING EDGES AND DIHEDRAL ANGLES OF 0° AND 45°

摘要

An experimental investigation was conducted to evaluate the heat-transfer characteristics of two 60° swept delta wings with cylindrical leading edges of 0.25-inch radii and dihedral angles of 0° and 45°. The tests were conducted at a Mach number of 4.95 and a stagnation temperature of 400° F. The test-section unit Reynolds number was varied from 1.95 X 106 to 12.24 X 106 per foot.nThe results of the investigation indicated that, in a plane normal to the leading edge, the laminar-flow heat-transfer distribution was in good agreement with two-dimensional blunt-body theory. The stagnation-line heat-transfer level could be predicted from two-dimensional blunt-body theory provided the stagnation-line heat-transfer coefficient was assumed to vary as the cosine of the effective sweep.nA comparison of the heating rates to the 0° dihedral wing (planform sweep of 60°) and the 45° dihedral wing (planform sweep of 69.3°) with equal panel sweep and panel area indicated that the stagnation-line heat-transfer coefficient for the 45° dihedral wing could be as much as 40 percent less than the stagnation-line heat-transfer coefficient for the 0° dihedral wing at both equal angles of attack and equal lifts. The laminar-flow heat-transfer rate to both wings outside the vicinity of the stagnation line was essentially equal.