CALCULATION OF THREE-DIMENSIONAL UNSTEADY TRANSONIC FLOWS PAST HELICOPTER BLADES.

被引：0
|
作者：
Chattot, J.J.
机构：
来源：
NASA Technical Paper | 1980年 / 1721期
关键词：
AERODYNAMICS - Wings and Airfoils;
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摘要：
A finite difference code for predicting the high-speed flow over the advancing helicopter rotor is presented. The code solves the low-frequency, transonic small disturbance equation and is suitable for modeling the effects of advancing blade unsteadiness on blades of nearly arbitrary planform. Computed results show good agreement with experimental blade pressure data.
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