Abstract
The various design parameters which affect the performance versus speed of the compound helicopter are studied, such as disk loading, solidity, and tip speed schedule. Additional variables which are part of the compound design, such as propeller diameter, wing lift, and equivalent drag, are similarly studied. The interrelationship of each parameter is shown in terms of the total lift/propulsive power required. The study further presumes a fixed mission requirement against which each parameter is evaluated and optimized based on proper sizing and fuel usage. The study includes the direct effect of engine power/weight ratio and SFC. The paper lays a foundation for future performance analyses of this hybrid vehicle.
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