## Use of potential flow theory to evaluate subsonic inlet data from a simulator-powered nacelle at cruise conditions |

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additive drag coefficients analysis boundary layer boundary-layer effect capture stream tube Circum Comparison of theoretical compressibility correction compressibility effects compressible flow theory compressible velocity corrected for compressibility cowl drag coefficients cowl drag force cowl external surface cowl pressure distributions density Dimensionless axial location discrepancies distributions at free-stream effects of mass-flow experimental cowl internal experimental pressure distributions external cowl external surface static-pressure Figure 17 flow rate flow ratio free-stream Mach 0.75 free-stream Mach number highest mass-flow incompressible indicated inlet additive drag inlet and boattail inlet choked inlet drag coefficients inlet highlight inlet mass inlet mass-flow ratio internal cowl pressure internal pressure distributions Lewis Research Center maximum nacelle NACA NASA TM number of 0.60 one-dimensional compressible flow POTENTIAL FLOW THEORY ratio and free-stream shown in figure stagnation point stagnation-point location static pressure SUBSONIC INLET surface static-pressure distributions theoretical and experimental theoretical pressure distributions theoretical results Turbofan weight flow wind tunnel