Technical Note - National Advisory Committee for Aeronautics
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 1322 |
| Release | : 1956 |
| Genre | : Aeronautics |
| ISBN | : |
Wing Body Interference At Supersonic Speeds
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Experimental Pressure Distributions Over Two Wing-body Combinations at Mach Number 1.9
| Author | : Barry Moskowitz |
| Publisher | : |
| Total Pages | : 40 |
| Release | : 1951 |
| Genre | : Aerodynamics |
| ISBN | : |
Abstract: Pressure distributions on two wing-body combinations were obtained at Mach number of 1.9 to investigate wing-body interference. A rectangular wing, a triangular wing, and a cylindrical body having an ogive nose were investigated alone and in combination. Pressure distributions over the wing body combination compared favorable with theoretical calculations based primarily on a generalization of the method of Nielsen and Matteson, except at the root section of wings where boundary layer of body modified the flow.
An Analysis of the Stability and Ultimate Compressive Strength of Short Sheet-stringer Panels with Special Reference to the Influence of the Riveted Connection Between Sheet and Stringer
| Author | : Benjamin H. Beam |
| Publisher | : |
| Total Pages | : 312 |
| Release | : 1955 |
| Genre | : Aerodynamics |
| ISBN | : |
General Theory of Wave-drag Reduction for Combinations Employing Quasi-cylindrical Bodies with an Application to Swept-wing and Body Combinations
| Author | : Jack N. Nielsen |
| Publisher | : |
| Total Pages | : 82 |
| Release | : 1955 |
| Genre | : Aeronautics |
| ISBN | : |
The wing-body interference theory of NACA TN 2677 applied to symmetrical wings in combination with quasi-cylindrical bodies permits the direct calculation of pressure-distribution changes produced by body shape changes. This theory is used to determine the relative magnitued of the wave-drag reduction produced by changes in cylinder cross-sectional area and that produced changes in cross-sectional shape (without change in area). The body distortion is expressed as a Fourier series, and an integral equation is derived for the body shape for minimum drag for each Fourier component. Thus the wave-drag reductions for the various Fourier harmonics are independent and additive.
Monthly Catalog of United States Government Publications
| Author | : United States. Superintendent of Documents |
| Publisher | : |
| Total Pages | : 1640 |
| Release | : 1956 |
| Genre | : Government publications |
| ISBN | : |
Index of NACA Technical Publications
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 580 |
| Release | : 1956 |
| Genre | : Aeronautics |
| ISBN | : |
Annual Report of the National Advisory Committee for Aeronautics
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 988 |
| Release | : 1950 |
| Genre | : Aeronautics |
| ISBN | : |
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Experimental Investigation of a 90 Degree Cascade Diffusing Bend with an Area Ratio of 1.45:1 and with Several Inlet Boundary Layers
| Author | : Daniel Friedman |
| Publisher | : |
| Total Pages | : 804 |
| Release | : 1952 |
| Genre | : Aerodynamics |
| ISBN | : |
An experimental investigation was conducted in order to determine the performance of a 90 degree cascade diffusing bend with an area ratio of 1.45:1 and a 19-inch square inlet with several inlet-boundary-layer shapes and thicknesses. The maximum mean inlet Mach number was 0.41 and the corresponding airfoil Reynolds number was 950,000. The experimental results seem to indicate that, when the duct configuration requires a bend, a certain amount of diffusion can be obtained without an appreciable rise in the total-pressure losses. If length is important, this configuration requires much less space than the usual diffuser-bend combination.
