CALCULATION OF THE LOAD DISTRIBUTION, AT SUPERSONIC SPEEDS, ON A SWEPTBACK WING OF ARBITRARY PLANFORM.
ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND)
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A method for calculating the load distribution on a cambered or uncambered sweptback wing, with subsonic leading edges and supersonic or subsonic trailing edges, is described. Evvards method is used for the part of the wing ahead of the trailing edge disturbances, and a lift cancellation method for the part affected by the wake. The formulae derived are put into forms suitable for calculations on a high-speed digital computer. Author
- Fluid Mechanics