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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Calculation of aerodynamic forces on a propeller in pitch or yaw

Calculation of aerodynamic forces on a propeller in pitch or yaw

Date: February 15, 1949
Creator: Crigler, John L & Gilman, Jean, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 I : maximum thickness at 20 percent of the chord

Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 I : maximum thickness at 20 percent of the chord

Date: November 19, 1948
Creator: Berggren, Robert E & Summers, James L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Longitudinal stability and control characteristics of a semispan airplane model at transonic speeds as obtained by the transonic-bump method

Longitudinal stability and control characteristics of a semispan airplane model at transonic speeds as obtained by the transonic-bump method

Date: July 19, 1948
Creator: Weil, Joseph & Spearman, M Leroy
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of aerodynamic hysteresis on critical flutter speed at stall

Effect of aerodynamic hysteresis on critical flutter speed at stall

Date: June 18, 1948
Creator: Mendelson, Alexander
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental study of loop-scavenged compression-ignition cylinder for gas-generator use

Experimental study of loop-scavenged compression-ignition cylinder for gas-generator use

Date: April 4, 1949
Creator: Foster, Hampton H; Tauschek, Max J & Schuricht, F Ralph
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Wind-Tunnel Tests of Triangular and Rectangular Wings in Steady Roll at Mach Numbers of 1.62 and 1.92

Preliminary Wind-Tunnel Tests of Triangular and Rectangular Wings in Steady Roll at Mach Numbers of 1.62 and 1.92

Date: February 17, 1949
Creator: Brown, Clinton E & Heinke, Harry S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Lateral and directional stability and control characteristics of a C-54D airplane

Lateral and directional stability and control characteristics of a C-54D airplane

Date: March 24, 1949
Creator: Talmage, Donald B & Reeder, John P
Description: Data are presented showing compliance of C-54D with Army and Navy lateral and directional stability and control specifications. The airplane met requirements except for the rolling effectiveness pb/2V, the aileron forces in rolling, and the rudder forces in the asymmetric power conditions which were marginal. Also, the results of special tests concerning asymmetric power, asymmetric loading, and pitch due to yaw requested by the Airplane Handling Qualities Subcommittee of the Air Transport Association are presented.
Contributing Partner: UNT Libraries Government Documents Department
An investigation of aileron oscillations at transonic speeds on NACA 23012 and NACA 65-212 airfoils by the wing-flow method

An investigation of aileron oscillations at transonic speeds on NACA 23012 and NACA 65-212 airfoils by the wing-flow method

Date: December 29, 1948
Creator: Crane, Harold L
Description: An investigation is being conducted to determine the feasibility of studying aileron buzz by means of the wing-flow method. Two semispan models which had an aspect ratio of 6 and a taper ratio of 2 with quarter-chord half-span mass-balanced ailerons have been used. One had an NACA 23012 airfoil section and the second, an NACA 65-212 airfoil section. The ailerons on both models were subject to buzz over a small range of Mach number near 0.9. Data obtained by wing-flow testing agreed reasonably well with full-scale flight results.
Contributing Partner: UNT Libraries Government Documents Department
Effect of centrifugal force on critical flutter speed on a uniform cantilever beam

Effect of centrifugal force on critical flutter speed on a uniform cantilever beam

Date: June 18, 1948
Creator: Mendelson, Alexander
Description: Semirigid flutter theory is used. Calculations are made on airfoils with fundamental bending frequencies up to 2000 radian per second. Centrifugal force can under certain conditions reduce the critical flutter speed.
Contributing Partner: UNT Libraries Government Documents Department
NACA investigation of fuels corresponding to specification AN-F-58 : results of studies in single combustors of J-33, J-34, J-35, and NENE turbojet engines

NACA investigation of fuels corresponding to specification AN-F-58 : results of studies in single combustors of J-33, J-34, J-35, and NENE turbojet engines

Date: November 16, 1945
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department