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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Results 15251 - 15274 of 19,794
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Section characteristics of an NACA 0006 airfoil with area suction near the leading edge

Section characteristics of an NACA 0006 airfoil with area suction near the leading edge

Date: January 1, 1954
Creator: Weiberg, James A & Dannenberg, Robert E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The similarity law for nonsteady hypersonic flows and requirements for the dynamical similarity of related bodies in free flight

The similarity law for nonsteady hypersonic flows and requirements for the dynamical similarity of related bodies in free flight

Date: February 1, 1952
Creator: Hamaker, Frank M & Wong, Thomas J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A modified Reynolds analogy for the compressible turbulent boundary layer on a flat plate

A modified Reynolds analogy for the compressible turbulent boundary layer on a flat plate

Date: March 1, 1953
Creator: Rubesin, Morris W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Minimum wave drag of bodies of revolution with a cylindrical center section

Minimum wave drag of bodies of revolution with a cylindrical center section

Date: October 1, 1951
Creator: Fuller, Franklyn B & Briggs, Benjamin R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A method for predicting the upwash angles induced at the propeller plane of a combination of bodies with an upswept wing

A method for predicting the upwash angles induced at the propeller plane of a combination of bodies with an upswept wing

Date: October 1, 1951
Creator: Yaggy, Paul F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Minimum wave drag for arbitrary arrangements of wings and bodies

Minimum wave drag for arbitrary arrangements of wings and bodies

Date: February 1, 1956
Creator: Jones, Robert T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The minimization of wave drag for wings and bodies with given base area or volume

The minimization of wave drag for wings and bodies with given base area or volume

Date: July 1, 1957
Creator: Heaslet, Max A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Reduction of profile drag at supersonic velocities by the use of airfoil sections having a blunt trailing edge

Reduction of profile drag at supersonic velocities by the use of airfoil sections having a blunt trailing edge

Date: September 1, 1955
Creator: Chapman, Dean R
Description: A preliminary theoretical and experimental investigation has been made on the aerodynamic characteristics of blunt-trailing-edge airfoils at supersonic velocities. The theoretical considerations indicate that properly designed airfoils with moderately blunt trailing edges can have less profile drag, greater lift-curve slope, and high maximum lift-drag ratio than conventional sections. These predictions have been substantiated by experimental measurements on airfoils of 10-percent-thickness ratio at Mach numbers of 1.5 and 2.0, and at Reynolds numbers between 0.2 and 1.2 million.
Contributing Partner: UNT Libraries Government Documents Department
Reduction of profile drag at supersonic velocities by the use of airfoil sections having a blunt trailing edge

Reduction of profile drag at supersonic velocities by the use of airfoil sections having a blunt trailing edge

Date: November 1, 1949
Creator: Chapman, Dean R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The resistance to air flow of porous materials suitable for boundary-layer-control applications using area suction

The resistance to air flow of porous materials suitable for boundary-layer-control applications using area suction

Date: January 1, 1954
Creator: Dannenberg, Robert E; Weiberg, James A & Gambucci, Bruno J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Review of some recent data on buffet boundaries

Review of some recent data on buffet boundaries

Date: May 23, 1951
Creator: Purser, Paul E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the effects upon lift of a gap between wing and body of a slender wing-body combination

Theoretical investigation of the effects upon lift of a gap between wing and body of a slender wing-body combination

Date: August 1, 1954
Creator: Dugan, Duane W & Hikido, Katsumi
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the supersonic lift and drag of thin, sweptback wings with increased sweep near the root

Theoretical investigation of the supersonic lift and drag of thin, sweptback wings with increased sweep near the root

Date: June 1, 1953
Creator: Cohen, Doris & Friedman, Morris D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A semi-empirical method for calculating the pitching moment of bodies of revolution at low Mach numbers

A semi-empirical method for calculating the pitching moment of bodies of revolution at low Mach numbers

Date: May 17, 1951
Creator: Hopkins, Edward J
Description: A semiempirical method, in which potential theory is arbitrarily combined with an approximate viscous theory, for calculating the aerodynamic pitching moments for bodies of revolution is presented. The method can also be used for calculating the lift and drag forces. The calculated and experimental force and moment characteristics of 15 bodies of revolution are compared.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of stage performance of X24C-2 ten-stage axial-flow compressor at design speed

Investigation of stage performance of X24C-2 ten-stage axial-flow compressor at design speed

Date: May 22, 1950
Creator: Finger, Harold B; Cohen, Leo & Stewart, Warner L
Description: The stage performance of the X24C-2 axial-flow compressor, as determined from radial distributions of total pressure and temperature measured in each stator-blade row, was investigated at design speed at weight flows corresponding to those of the maximum weight-flow, peak-efficiency, and surge points. The stage performance is presented as the measured stage pressure ratios and the calculated velocity diagrams. The average stage total-pressure ratio at the surge operating condition in the first stage was approximately 1.10; in the second stage, approximately 1.13; and in all remaining stages, approximately constant at a value of 1.15. Regions of inefficient flow are discussed so as to point out the reasons for the poor flow conditions.
Contributing Partner: UNT Libraries Government Documents Department
Efficiency of radial-flow turbine of Turbo Engineering Corporation TT13-18 turbosupercharger

Efficiency of radial-flow turbine of Turbo Engineering Corporation TT13-18 turbosupercharger

Date: January 1, 1948
Creator: Coulter, Earl E. & Galloway, William R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics throughout the subsonic speed range of a thin, sharp-edged horizontal tail of aspect ratio 4 equipped with a constant-chord elevator

The aerodynamic characteristics throughout the subsonic speed range of a thin, sharp-edged horizontal tail of aspect ratio 4 equipped with a constant-chord elevator

Date: June 30, 1949
Creator: Bandettini, Angelo & Reed, Verlin D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic effects of rockets and fuel tanks mounted under the swept-back wing of an airplane model

The aerodynamic effects of rockets and fuel tanks mounted under the swept-back wing of an airplane model

Date: April 23, 1948
Creator: Boddy, Lee E & Morrill, Charles P , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section

Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section

Date: November 1, 1954
Creator: Sacks, Alvin H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic loads on a leading-edge flap and a leading-edge slat on the NACA 64A010 airfoil section

Aerodynamic loads on a leading-edge flap and a leading-edge slat on the NACA 64A010 airfoil section

Date: June 1, 1954
Creator: Kelly, John A & Mccullough, George B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Axially symmetric shapes with minimum wave drag

Axially symmetric shapes with minimum wave drag

Date: February 1, 1955
Creator: Heaslet, Max A & Fuller, Franklyn, B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Behavior of vortex system behind cruciform wings - motions of fully rolled-up vortices

Behavior of vortex system behind cruciform wings - motions of fully rolled-up vortices

Date: January 1, 1952
Creator: Sacks, Alvin H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : aerodynamic characteristics in sideslip of a large-scale model having a 63 degree swept-back vertical tail

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : aerodynamic characteristics in sideslip of a large-scale model having a 63 degree swept-back vertical tail

Date: October 7, 1949
Creator: Mccormack, Gerald M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics for symmetrical wing sections at high subsonic and moderate supersonic Mach numbers

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics for symmetrical wing sections at high subsonic and moderate supersonic Mach numbers

Date: July 7, 1949
Creator: Mas, Newton A
Description: None
Contributing Partner: UNT Libraries Government Documents Department