Navier-Stokes and Potential Theory Solutions for a Helicopter Fuselage and Comparison With Experiment

The use of trademarks or names of manufacturers in this report is for accurate reporting and does not constitute an ocial endorsement, either expressed or implied, of such products or manufacturers by the National Aeronautics and Space Administration. Summary Two computational methods are used to predict the ow over a generic helicopter fuselage of a simple conguration. A thin-layer Navier-Stokes code and a panel method code are used to compute the surface pressures for comparison with data from 4 experimental conditions at 14 fuselage stations. The ndings of both methods are in agreement with the experimental pressure data. However, separation patterns and other viscous ow features from the Navier-Stokes code solution are shown that cannot be easily modeled with the panel method.