National Advisory Committee for Aeronautics (NACA) - 239 Matching Results

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Analysis of pure-bending flutter of a cantilever swept wing and its relation to bending-torsion flutter

Description: From Introduction: "The present paper is intended to give some features of flutter in bending alone and contains results of analyses made to determine some effects of wing mass-density ratio, angle of sweepback, length-semichord ratio, and Mach number. Some relations of pure-blending flutter to the conventional bending-torsion flutter are also given."
Date: September 1951
Creator: Cunningham, H J
Partner: UNT Libraries Government Documents Department

Analytical evaluation of aerodynamic characteristics of turbines with nontwisted rotor blades

Description: From Introduction: "The purpose the present report is to investigate the aerodynamic characteristics of nontwisted-rotor-blade turbines and to evaluate the characteristics of this type of design by comparison with the characteristics of free-vortex designs."
Date: May 1951
Creator: Slivka, William R & Silvern, David H
Partner: UNT Libraries Government Documents Department

Analytical investigation of fully developed laminar flow in tubes with heat transfer with fluid properties variable along the radius

Description: From Introduction: "In the analytical investigation reported herein, which was conducted in the NACA Lewis laboratory, both velocity and temperature distribution are obtained for fully developed laminar flow in tubes of gases and of liquid metals with variable fluid properties."
Date: July 1, 1951
Creator: Deissler, Robert G
Partner: UNT Libraries Government Documents Department

Applicability of the hypersonic similarity rule to pressure distributions which include the effects of rotation for bodies of revolution at zero angle of attack

Description: The analysis of Technical Note 2250, 1950, is extended to include the effects of flow rotation. It is found that the theoretical pressure distributions over drive cylinders can be related by the hypersonic similarity rule with sufficient accuracy for most engineering purposes. The error introduced into pressure distributions and drag effective cylinders by ignoring the rotation term in the characteristic equations is investigated.
Date: June 1, 1951
Creator: Rossow, Vernon J.
Partner: UNT Libraries Government Documents Department

Approximate methods for calculating the flow about nonlifting bodies of revolution at high supersonic airspeeds

Description: Explicit expressions are developed which yield the Mach number and pressure distributions on the surfaces of pointed nonlifting bodies of revolution operating at high supersonic airspeeds and at values of the hypersonic similarity parameter (ratio of free-stream Mach number to slenderness ratio) greater than 1. Very simple explicit expressions are obtained for these distributions in the special case of slender bodies. In the case of cones, the analytic solutions accurately define the entire flow field over a wide range of free-stream Mach numbers and apex angles.
Date: December 1, 1951
Creator: Eggers, A J , Jr & Savin, Raymond C
Partner: UNT Libraries Government Documents Department