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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
An investigation of single- and dual-rotation propellers at positive and negative thrust, and in combination with an NACA 1-series D-type cowling at Mach numbers up to 0.84

An investigation of single- and dual-rotation propellers at positive and negative thrust, and in combination with an NACA 1-series D-type cowling at Mach numbers up to 0.84

Date: January 1, 1957
Creator: Reynolds, Robert M; Samonds, Robert I & Walker, John H
Description: An investigation has been made to determine the aerodynamic characteristics of the NACA 4-(5)(05)-041 four-blade, single-relation propeller and the NACA 4-(5)(05)-037 six- and eight-blade, dual-rotation propellers in combination with various spinners and NACA d-type spinner-cowling combinations at Mach numbers up to 0.84. Propeller force characteristics, local velocity distributions in the propeller planes, inlet pressure recoveries, and static-pressure distributions on the cowling surfaces were measured for a wide range of blade angles, advance ratios, and inlet-velocity ratios. Included are data showing: (a) the effect of extended cylindrical spinners on the characteristics of the single-rotation propeller, (b) the effect of variation of the difference in blade angle setting between the front and rear components of the dual-rotation propellers, (c) the negative- and static-thrust characteristics of the propellers with 1 series spinners, and (d) the effects of ideal- and platform-type propeller-spinner junctures on the pressure-recovery characteristics of the single-rotation propeller-spinner-cowling combination.
Contributing Partner: UNT Libraries Government Documents Department
An investigation of string support interference on base pressure and forebody chord force at Mach numbers from 0.60 to 1.30

An investigation of string support interference on base pressure and forebody chord force at Mach numbers from 0.60 to 1.30

Date: January 28, 1955
Creator: Tunnell, Phillips J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of some wake vortex characteristics of an inclined ogive-cylinder body at Mach number 1.98

Investigation of some wake vortex characteristics of an inclined ogive-cylinder body at Mach number 1.98

Date: August 23, 1955
Creator: Jorgensen, Leland H & Perkins, Edward W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of submerged air inlets on a 1/4-scale model of a typical fighter-type airplane

An investigation of submerged air inlets on a 1/4-scale model of a typical fighter-type airplane

Date: June 2, 1948
Creator: Delany, Noel K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of supersonic turbulent boundary layers on slender bodies of revolution in free flight by use of a Mach-Zehnder interferometer and shadowgraphs

An investigation of supersonic turbulent boundary layers on slender bodies of revolution in free flight by use of a Mach-Zehnder interferometer and shadowgraphs

Date: September 1, 1958
Creator: Seiff, Alvin & Short, Barbara J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of symmetric body indentations designed to reduce the transonic zero-lift wave drag of a 45 degree swept wing with an NACA 64A006 section and with a thickened leading-edge section

Investigation of symmetric body indentations designed to reduce the transonic zero-lift wave drag of a 45 degree swept wing with an NACA 64A006 section and with a thickened leading-edge section

Date: March 19, 1957
Creator: Holdaway, George H & Hatfield, Elaine W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurements of downwash and sidewash behind cruciform triangular wings at Mach number 1.4

Measurements of downwash and sidewash behind cruciform triangular wings at Mach number 1.4

Date: April 4, 1951
Creator: Wetzel, Benton E & Pfyl, Frank A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurements in flight of the stability, lateral control, and stalling characteristics of an airplane equipped with full-span Zap flaps and spoiler-type ailerons

Measurements in flight of the stability, lateral control, and stalling characteristics of an airplane equipped with full-span Zap flaps and spoiler-type ailerons

Date: December 1, 1943
Creator: Christophersen, Don R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurements in flight of the pressure distribution on the right wing of a P-39N-1 airplane at several values of Mach number

Measurements in flight of the pressure distribution on the right wing of a P-39N-1 airplane at several values of Mach number

Date: April 1, 1945
Creator: Rolls, L Stewart
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurements of section characteristics of a 45 degree swept wing spanning a rectangular low-speed wind tunnel as affected by the tunnel walls

Measurements of section characteristics of a 45 degree swept wing spanning a rectangular low-speed wind tunnel as affected by the tunnel walls

Date: August 1, 1950
Creator: Dannenberg, Robert E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurements of the damping in roll of large-scale swept-forward and swept-back wings

Measurements of the damping in roll of large-scale swept-forward and swept-back wings

Date: July 30, 1947
Creator: Hunton, Lynn W & Dew, Joseph K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurements of the effects of wall outflow and porosity on wave attenuation in a transonic wind tunnel with perforated walls

Measurements of the effects of wall outflow and porosity on wave attenuation in a transonic wind tunnel with perforated walls

Date: August 1, 1958
Creator: Spiegel, Joseph M; Tunnell, Phillips J & Wilson, Warren S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurements of the nonlinear variation with temperature of heat-transfer rate from hot wires in transonic and supersonic flow

Measurements of the nonlinear variation with temperature of heat-transfer rate from hot wires in transonic and supersonic flow

Date: April 1, 1957
Creator: Winovich, Warren & Stine, Howard A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurements of the pressure distribution on the horizontal-tail surface of a typical propeller-driven pursuit airplane in flight I : effects of compressibility in steady straight and accelerated flight

Measurements of the pressure distribution on the horizontal-tail surface of a typical propeller-driven pursuit airplane in flight I : effects of compressibility in steady straight and accelerated flight

Date: July 1, 1947
Creator: Sadoff, Melvin; Turner, William N & Clousing, Lawrence A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of axially symmetric flow over steps at transonic speeds with comparisons of estimated and experimental drag results

Investigation of axially symmetric flow over steps at transonic speeds with comparisons of estimated and experimental drag results

Date: July 22, 1957
Creator: Holdaway, George H & Wallace, Minor R , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of boundary-layer transition on flat-faced bodies of revolution at high supersonic speeds

Investigation of boundary-layer transition on flat-faced bodies of revolution at high supersonic speeds

Date: June 7, 1957
Creator: Canning, Thomas N & Sommer, Simon C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of downwash and wake characteristics at a Mach number of 1.53 I : rectangular wing

Investigation of downwash and wake characteristics at a Mach number of 1.53 I : rectangular wing

Date: March 1, 1949
Creator: Perkins, Edward W & Canning, Thomas N
Description: The results of an experimental investigation of the downwash and wake characteristics behind a rectangular plan-form wing of aspect ratio 3.5 are presented. The airfoil section was a 5-percent-thick, symmetrical double wedge. The tests were made at a Mach number of 1.53 and a Reynolds number of 1.25 million. A comparison between experimental and theoretical values of the downwash angles is made.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Diving Moments of a Pursuit Airplane in the Ames 16-Foot High Speed Wind Tunnel

Investigation of Diving Moments of a Pursuit Airplane in the Ames 16-Foot High Speed Wind Tunnel

Date: October 7, 1942
Creator: Erickson, Albert L
Description: A pursuit type airplane encountered severe diving moments in high-speed dives which make recovery difficult. For the purpose of investigating these diving moments and finding means for their reduction, a 1/6-scale model of the airplane was tested in the 16-foot high-speed wind tunnel at Ames Aeronautical Laboratory. The test results indicate that up to a Mach number of at least 0.75, the limit of the tests, the dive-recovery difficulties can be alleviated and the longitudinal maneuverability improved by the substitution of a long symmetrical fuselage for the standard fuselage.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of downwash and wake characteristics at a Mach number of 1.53 II : triangular wing

Investigation of downwash and wake characteristics at a Mach number of 1.53 II : triangular wing

Date: June 6, 1949
Creator: Perkins, Edward W & Canning, Thomas N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of drag and pressure recovery of a scoop inlet in the transonic speed range

Investigation of drag and pressure recovery of a scoop inlet in the transonic speed range

Date: December 15, 1952
Creator: Selna, James; Bright, Loren G & Schlaff, Bernard A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of lift and center of pressure of low-aspect-ratio, cruciform, triangular, and rectangular wings in combination with a slender fuselage at high supersonic speeds

Investigation of lift and center of pressure of low-aspect-ratio, cruciform, triangular, and rectangular wings in combination with a slender fuselage at high supersonic speeds

Date: June 26, 1952
Creator: Canning, Thomas N & Denardo, Billy Pat
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of downwash and wake characteristics at a Mach number of 1.53 III : swept wings

Investigation of downwash and wake characteristics at a Mach number of 1.53 III : swept wings

Date: February 23, 1950
Creator: Perkins, Edward W & Canning, Thomas N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of local heat-transfer and pressure drag characteristics of a yawed circular cylinder at supersonic speeds

Investigation of local heat-transfer and pressure drag characteristics of a yawed circular cylinder at supersonic speeds

Date: January 24, 1956
Creator: Goodwin, Glen; Creager, Marcus O & Winkler, Ernest L
Description: Local heat-transfer coefficients, temperature recovery factors, and pressure distributions were measured on the front side of a circular cylinder at a nominal Mach number of 3.9 over a range of free-stream Reynolds numbers from 2.1 x 10 to the 3rd power to 6.7 x 10 to the 3rd power and yaw angles from zero degrees to 44 degrees. Yawing the cylinder reduced the heat-transfer coefficients and the pressure drag coefficients. The amount of reduction may be predicted by a theory presented herein.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition

Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition

Date: January 1, 1958
Creator: Chapman, Dean R; Kuehn, Donald M & Larson, Howard K
Description: Report presents the results of experimental and theoretical research conducted on flow separation associated with steps, bases, compression corners, curved surfaces, shock-wave boundary-layer reflections, and configurations producing leading-edge separation. Results were obtained from pressure-distribution measurements, shadowgraph observations, high-speed motion pictures, and oil-film studies. The maximum scope of measurement encompassed Mach numbers between 0.4 and 3.6, and length Reynolds numbers between 4,000 and 5,000,000.
Contributing Partner: UNT Libraries Government Documents Department