Abstract
The drag coefficient of the nacelle lip-skin model was investigated to analyze the aerodynamic performance of the bias acoustic liner underneath the nacelle lip-skin at lowspeed free stream velocities. Drag coefficient reduction, using the bias flow of a bias acoustic liner on a nacelle lip-skin, is discussed for incompressible flow condition. The experimental data were recorded to analyze the nacelle lip-skin’s drag coefficients. The investigation covered four different bias flow areas to total nacelle lip-skin area ratios, ranging from 0 % to 12 %, at Reynolds numbers ranging from 2.2×105 to 3.5×105 and the nacelle internal static pressure of 0- 90 Pa, with the uncertainty of the experimental data being less than 10 %. The results show that the drag coefficient is reduced by up to 19 % as the ratio of the bias flow area to the total nacelle lip-skin area increases from 0 % to 12 %. In the transition flow regime, the drag coefficient increases gradually with Reynolds number. In addition, the optimum nacelle internal static pressure of present study was found to be 60 Pa.
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