National Advisory Committee for Aeronautics (NACA) - 2 Matching Results

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An empirically derived method for calculating pressure distribution at supercritical Mach numbers and moderate angles of attack

Report presenting a procedure for calculating pressure distributions over airfoils at supercritical Mach numbers. Only the forward portion of the airfoil, where interaction between local boundary-layer thickness and local-pressure distribution is negligible, is considered in detail. The method cannot be considered definitive because it requires that certain characteristics regarding pressure distributions and geometric properties be known.

Date: April 1, 1947

Creator: Nitzberg, Gerald E. & Sluder, Loma E.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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Velocity distributions on two-dimensional wing-duct inlets by conformal mapping

The conformal-mapping method of the Cartesian mapping function is applied to the determination of the velocity distribution on arbitrary two-dimensional duct-inlet shapes such as are used in wing installations. An idealized form of the actual wing-duct inlet is analyzed. The effects of leading edge stagger, inlet-velocity ratio, and section lift coefficients on the velocity distribution are included in the analysis. Numerical examples are given and, in part, compared with experimental data.