Theoretical Analysis of Flows Around Helicopter Fuselages Application to Design and Development,
AEROSPATIALE MARIGNANE (FRANCE) DIV HELICOPTERES
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This paper describes three dimensional aerodynamic calculations as applied to fuselage design in the Aerospatiale Helicopter Division. Three levels of complexity may be distinguished in the calculation programs 1 a singularities method describing the potential flow around a fuselage, 2 an integral three dimensional boundary layer method for predicting three dimensional separations, and 3 a point vortex wake model. The first two methods are routinely used with very short response times, either on complete fuselages or for specific aircraft sections. Close agreement is obtained with the available experimental results. Various examples are given of applications to project or development work. Operational calculations cannot yet be performed with the wake model, as the method is still under development. In the current state of the art, aerodynamic calculations provide undeniable services but can by no means replace wind tunnel tests for determining complete aircraft drag.