## Pressure distributions at Mach number 2.05 on a series of highly swept arrow wings employing various degrees of twist and camber |

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9 x'/c Upper Airfoils ajnssajd angle of attack ARROW WINGS EMPLOYING aspect ratio axial-force coefficient axial-force distribution b/2 Wing benefits of twist CL theory Comparison of theoretical DEGREES OF TWIST design lift coefficient design methods chosen discrepancies distance from wing drag in compari EMPLOYING VARIOUS DEGREES Experiment Theory foot supersonic pressure force data HIGHLY SWEPT ARROW I I I I I I Langley leading-edge suction lift-drag ratio condition loading curve Lower Upper Lower MACH NUMBER 2.05 maximum lift-drag ratio normal-force distributions number of 2.05 ooa k OOOOOOOOOOO ooooo ooooooooooo d0 phenomena and shock-induced pressure data previous force tests ratio of 2.2k reflection plate section normal-force coefficient shock-induced flow separation shown in figure SWEPT ARROW WINGS TABULATED PRESSURE COEFFICIENTS Technical Memorandum X-332 tests substantiate previous theoretical and experimental twist and camber Upper Lower Upper Upper surface vortex flow originating wing apex WINGS EMPLOYING VARIOUS x'/c Upper Lower