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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Restricted Report
 Collection: Technical Report Archive and Image Library
Comparison of Wind-Tunnel and Flight Measurements of Stability and Control Characteristics of a Douglas A-26 Airplane

Comparison of Wind-Tunnel and Flight Measurements of Stability and Control Characteristics of a Douglas A-26 Airplane

Date: March 1, 1946
Creator: Koven, William & Kayten, Gerald G.
Description: Tests in Langley pressure tunnel of model XA-26 bomber were compared with those of A-26B (twin-engine attack bomber) and showed that static longitudinal stability, indicated by elevator-fixed neutral points, and variation of elevator deflection in straight and turning flight were good. Airplane possessed improved stability at low speeds which was attributed to pronounced stalling at root of production wing. At rudder-force reversal at speeds higher than those in flight tests, agreement in rudder-fixed and rudder-free static directional stability was good. Hinge moment obtained at zero sideslip was satisfactory for determining aileron forces in sideslip.
Contributing Partner: UNT Libraries Government Documents Department
Comparisons of methods of computing bending moments in helicopter rotor blades in the plane of flapping

Comparisons of methods of computing bending moments in helicopter rotor blades in the plane of flapping

Date: August 1, 1945
Creator: Luecker, Arthur R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Compressibility and heating effects on pressure loss and cooling of a baffled cylinder barrel

Compressibility and heating effects on pressure loss and cooling of a baffled cylinder barrel

Date: July 1, 1944
Creator: Ellerbrock, Herman H , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Compressibility Effects on Heat Transfer and Pressure Drop in Smooth Cylindrical Tubes

Compressibility Effects on Heat Transfer and Pressure Drop in Smooth Cylindrical Tubes

Date: October 1, 1944
Creator: Nielsen, Jack N
Description: An analysis is made to simplify pressure-drop calculations for nonadiabatic and adiabatic friction flow of air in smooth cylindrical tubes when the density changes due to heat transfer and pressure drop are appreciable. Solutions of the equation of motion are obtained by the use of Reynolds' analogy between heat transfer and skin friction. Charts of the solutions are presented for making pressure-drop calculations. A technique of using the charts to determine the position of a normal shock in a tube is described.
Contributing Partner: UNT Libraries Government Documents Department
Compressible potential flow with circulation about a circular cylinder

Compressible potential flow with circulation about a circular cylinder

Date: January 1, 1944
Creator: Heaslet, Max A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Compressive Strength of Flat Panels with Z- and Hat-Section Stiffeners

Compressive Strength of Flat Panels with Z- and Hat-Section Stiffeners

Date: June 1, 1944
Creator: Kotanchik, Joseph; Weinberger, Robert A.; Zender, George W. & Neff, John, Jr.
Description: Compression tests were conducted on 247 panels with Z-section stiffeners and 304 panels with hat-section stiffeners. Specimens were constructed from artificially aged Alclad 24S aluminum alloy with minimum guaranteed yield strengths of 64 and 57 ksi for stiffeners and sheet materials, respectively. Height, thickness, and spacing of stiffeners, sheet thickness, and length of specimens were varied systematically to show effects of changes in these dimensions on panel strength. Results show average stresses at buckling load and maximum load.
Contributing Partner: UNT Libraries Government Documents Department
Compressive strength of flat panels with Z-section stiffeners

Compressive strength of flat panels with Z-section stiffeners

Date: February 1, 1944
Creator: Dobrowski, Charles V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The conformal transformation of an airfoil into a straight line and its application to the inverse problem of airfoil theory

The conformal transformation of an airfoil into a straight line and its application to the inverse problem of airfoil theory

Date: December 1, 1944
Creator: Mutterperl, William
Description: A method of conformal transformation is developed that maps an airfoil into a straight line, the line being chosen as the extended chord line of the airfoil. The mapping is accomplished by operating directly with the airfoil ordinates. The absence of any preliminary transformation is found to shorten the work substantially over that of previous methods. Use is made of the superposition of solutions to obtain a rigorous counterpart of the approximate methods of thin-airfoils theory. The method is applied to the solution of the direct and inverse problems for arbitrary airfoils and pressure distributions. Numerical examples are given. Applications to more general types of regions, in particular to biplanes and to cascades of airfoils, are indicated. (author).
Contributing Partner: UNT Libraries Government Documents Department
Construction of wire strain gages for engine application

Construction of wire strain gages for engine application

Date: December 1, 1943
Creator: Tucker, Maurice
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Continuous use of internal cooling to suppress knock in aircraft engines cruising at high power

Continuous use of internal cooling to suppress knock in aircraft engines cruising at high power

Date: August 1, 1944
Creator: Bell, Arthur H
Description: None
Contributing Partner: UNT Libraries Government Documents Department