A wind tunnel test of a generic helicopter fuselage model with an independently mounted rotor has been conducted to obtain steady and periodic pressure data on the helicopter body. The model was tested at four advance ratios and three thrust coefficients. The periodic unsteady pressure coefficients are marked by four peaks associated with the passage of the four rotor blades. Blade passage effects are largest on the nose and tail boom of the model. The magnitude of the pulse increases with rotor thrust coefficient. Tabular listings of the unsteady pressure data are included to permit independent analysis. A CD-rom containing the steady and unsteady pressure data presented in the report is available from the authors.
Steady and Periodic Pressure Measurements on a Generic Helicopter Fuselage Model in the Presence of a Rotor
2000-06-01
Report
Keine Angabe
Englisch
Helicopter Fuselage Active Flow Control in the Presence of a Rotor
British Library Conference Proceedings | 2014
|Helicopter Fuselage Vibrations Induced by the Rotor
British Library Conference Proceedings | 1996
|Helicopter fuselage vibrations induced by the rotor
British Library Conference Proceedings | 1996
|An unsteady helicopter rotor-fuselage aerodynamic interaction analysis
Tema Archiv | 1990
|