The velocity field at the plane of the rotor disk of the V‐22 tilt rotor is analyzed using a detailed fuselage/wing/narelle panel method. The resultant rotor inflow velocities are then providrd to an aeroelastic rotor analysis to determine the aerodynamic proprotor loads induced
by the wing during airplane mode flight. It is shown that higher frequency blade loads are accurately predicted when the wing/rotor interference effects are included in a conventional aeroelastic rotor analysis. Sensitivities to parameters such as airspeed, angle of attack, and proprotor to
wing spacing are discussed. Correlation of oscillatory blade loads is shown between theory and wind tunnel data for the 0.2 scale V‐22 aeroelastic model. Comparisons are also shown with an analysis which uses a Joukowsky transformation technique to calculate the induced flow field with
superposition of the effects of wing thickness and circulation. The latter method is shown to be a good approximation to the complex flow conditions.
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Document Type: Research Article
Bell Helicopter Textron, Fort Worth, Tex.
Publication date: 1989-01-01
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