Abstract
Some of the more important results of a series of wind-tunnel investigations conducted at the Jet Propulsion Laboratory to determine the aerodynamic-force characteristics of delta wings are presented. A family of five delta wings was designed to cover the range of slope ratios, leading-edge slope to Mach wave slope, from 0.15 to 4.1. Lift or normal-force characteristics for these wings were systematically studied as a function of Reynolds Number and Mach Number. The results of these investigations are presented as normal-force coefficients per radian for the Mach Number range 1.33 to 4.55. These measurements are compared with the linear theor}^ both as a function of Mach Number and slope ratio. I t was found that the experimental measurements were in good agreement with and exhibited the trend of the theory in the range of slope ratios 0.15 to 0.70; whereas notable departures from the theory were observed for slope ratios greater than 0.70. For a given wing the systematic variation of the wing profile indicated that there existed a much greater dependence of the lift on profile or edge configuration than on Reynolds Number for slope ratios greater than 0.70.
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