The Calculation Of Generalised Forces On Oscillating Wings In Supersonic Flow By Lifting Surface Theory

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The plane problem of the vibrating airfoil in supersonic flow is dealt with and solved within the scope of a linearized theory by the method of the acceleration potential.

Geared toward advanced undergraduates and graduate students, this outstanding text surveys aeroelastic problems, their historical background, basic physical concepts, and the principles of analysis.

Beginning with no. 650 each hundredth number contains a list of the Reports and memoranda published since the last list.

Results of an investigation in the Langley full-scale tunnel of the induced flow near a lifting rotor are given. Measurements of stream angles and velocities were made in several transverse planes along and behind the rotor in four different conditions representative of the cruising and high-speed ranges of flight. These measurements indicate that available theory may be used to calculate with reasonable accuracy the induced flow over the forward three-quarters of the disk for these flight conditions provided that a realistic nonuniform rotor disk-load distribution is assumed. Rearward of the three-quarter-diameter point, calculations of the induced velocity are increasingly inaccurate due to the rolling up of the trailing-vortex system. Farther rearward, well behind the rotor, the flow may be represented more accurately by the flow behind a uniformly loaded wing.