Method for predicting the pressure distribution on swept wings with subsonic attached flow.
Abstract:ESDU 73012 presents an equation for the velocity at any point on the surface of a wing in compressible or incompressible subcritical flow. The formula applies for thickness/chord ratios up to 20 per cent, camber up to 3 per cent of chord, effective aspect ratios greater than 2.5 and effective sweeps less than 60 degrees. No boundary layer calculation is included. The physical significance of the various terms in the equation is explained, and tables and graphs give values for them to assist in calculating answers rapidly.
- Analogous Wing Concept
- Angle of Attack
- Kuchemann-Weber Formula
- Pressure Distribution
- Wing Cranks or Notches
- Wing-Body Combination
|Data Item ESDU 73012|
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