EFFECTS OF ROUNDING CORNERS AND LEADING EDGES ON THE WINDWARD-SURFACE PRESSURES OF A DELTA WING SWEPT 65° AT A MACH NUMBER OF 5.96 AT ANGLES OF ATTACK FROM 65° TO 115° AND ANGLES OF ROLL FROM 0° TO 25° AT 90° ANGLE OF ATTACK

摘要

Detailed pressures on the windward surface of two.flat-plate delta wings swept 65° and with rounded corners (one having square leading edges and the other having rounded leading edges) were obtained at a Mach number of 5.96 through an angle-of-attack range from 650 to 115° and at angles of roll from 0° to 25° at an angle of attack of 90°. These results were compared with those previously reported for a similar wing having sharp corners and square edges. At all atti¬tudes tested, any effect on the pressure distributions caused by rounding the corners only or by rounding the corners and leading edges was confined to about the last 10 percent of the radial rays emanating from the centroid of the model. The normal-force coefficient was essentially unaffected by rounding the corners only but was decreased by approximately 4 percent by rounding the corners and leading edges.