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An approximate method of calculating pressures in the tip region of a rectangular wing of circular-arc section at supersonic speeds

Description: From Introduction: "The present paper introduces the approximate method by means of which it is possible to calculate the pressures in the tip region of a rectangular with a symmetrical circular-arc section to a higher degree of accuracy than is possible with the usual linear methods."
Date: October 1950
Creator: Czarnecki, K. R. & Mueller, James N.
Partner: UNT Libraries Government Documents Department

Aerodynamics of a rectangular wing of infinite aspect ratio at high angles of attack and supersonic speeds

Description: From Introduction: "The present paper contains a first-order evaluation of a number of aerodynamic derivatives for a rectangular wing of infinite aspect ratio at finite angles of attack, based upon the linear perturbation theory for rotational flow."
Date: July 1955
Creator: Martin, John C. & Malvestuto, Frank S., Jr.
Partner: UNT Libraries Government Documents Department

Comparison Between Theoretical and Experimental Rates of Roll of Two Models with Flexible Rectangular Wings at Supersonic Speeds

Description: "A comparison is presented between the experimentally measured and theoretically calculated (by the method of NACA TN 3067) rates of roll of two rocket-propelled models with flexible rectangular wings. The comparisons show that although there are large aeroelastic losses in rolling rate, the theory predicts the actual rate of roll accurately" (p. 1).
Date: August 5, 1954
Creator: Hedgepeth, John M. & Kell, Robert J.
Partner: UNT Libraries Government Documents Department

Damping in roll of rectangular wings of several aspect ratios and NACA 65A-series airfoil sections of several thickness ratios at transonic and supersonic speeds as determined with rocket-powered models

Description: Report presenting rocket-powered flight tests to determine the damping in roll of rectangular wings of various aspect ratios and thickness ratios using NACA airfoil sections. The experimental damping in roll was consistently lower than what was predicted theoretically.
Date: August 24, 1950
Creator: Edmondson, James L.
Partner: UNT Libraries Government Documents Department

Pressure Measurements at Supersonic Speeds on a Section of a Rectangular Wing Having an NACA 65-009 Profile

Description: Report presenting an investigation of a rectangular wing with a subsonic-type round-leading-edge airfoil section (NACA 65-009) at various Mach numbers. The results generally agreed with calculated values with the exception of the laminar-separated region on the low-pressure surface of the model. Results regarding the calculation of pressure distribution, experimental pressure distributions, aerodynamic characteristics, and shadowgraph studies are provided.
Date: March 10, 1950
Creator: Rainey, Robert W.
Partner: UNT Libraries Government Documents Department