A 1/5‐scale semi‐span aeroelastic model of the Joint Services Vertical Lift Aircraft (JVX), now designated the V‐22, was tested in the NASA‐Langley Transonic Dynamics Tunnel (TDT). The Froude‐scaled model was initially configured in the V‐22
Stage I preliminary design proposal configuration. During the course of the two wind tunnel entries a number of design parameters were varied, including the hub design, blade bending stiffness, wing spar stiffness, rotor pitch‐flap coupling, and pylon
downstop configuration. The effect of compressibility was investigated by testing the model in both air and Freon. Aeroelastic stability, loads and vibration data were obtained for a wide range of airspeeds, rotor speeds and conversion angles. The results were used to provide a data base for
design of the V‐22 aircraft. The data were correlated with aeroelastic stability analyses to validate the analytical tools being used in the full‐scale design process.
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Document Type: Research Article
V-22 Rotor Dynamics, Bell Helicopter Textron, Fort Worth, Texas
Publication date: 1987-04-01
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