EXTENSION OF BLADE ELEMENT MOMENTUM THEORY TO INCORPORATE NONLINEAR LIFT AND DRAG COEFFICIENTS.

被引：0
|
作者：
Hodges, Dewey H.
机构：
来源：
Journal of the American Helicopter Society | 1980年 / 25卷 / 04期
关键词：
AERODYNAMICS - Wings and Airfoils - MATHEMATICAL TECHNIQUES - Perturbation Techniques;
D O I：
10.4050/jahs.25.48
中图分类号：
学科分类号：
摘要：
An expression for the steady induced inflow velocity is obtained from blade element and momentum theory considerations. The lift coefficient is allowed to be a quadratic function of angle of attack, and the drag coefficient, incorporated through a perturbation procedure, can be any arbitrary function of angle of attack. A principal range of interest is identified in which the function inflow versus blade pitch angle is single-valued. The results reduce to the classic formula found in the textbooks when the lift coefficient is linear and drag is ignored.
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页码：48 / 50
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