1958•NASA STI Repository (National Aeronautics and Space Administration)Requires access
An Analysis of Surface Pressures and Aerodynamic Load Distribution over the Swept Wing of the Douglas D-558-II Research Airplane at Mach Numbers from 0.73 to 1.73
N. V. Taillon
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Abstract
Report presenting the wing-section pressure-distribution and wing-panel load characteristics of the Douglas D-558-II airplane for a range of Mach numbers and airplane normal-force coefficients. At subsonic speeds, the pressure distributions are characterized by a high negative-pressure peak with an abrupt pressure recovery as a result of the leading-edge expansion over the upper surface at moderate angles of attack.