Nomogram for correcting drag and angle of attack of an airfoil model in an air stream of finite diameter
Nomogram for correcting drag and angle of attack of an airfoil model in an air stream of finite diameter
In experimenting with airfoil models in a wind tunnel, the magnitude of the forces acting on the model is affected by the fact that the air stream in which the model is suspended, has a restricted cross-section. In order to utilize the results for an airplane in an unlimited quantity of air, a correction must be made. The magnitude of this correction was determined by Prandtl by the application of his wing theory.
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Nomogram for correcting drag and angle of attack of an airfoil model in an air stream of finite diameter
1924-12-01
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