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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Some effects of body cross-sectional shape, including sunken-canopy design, on drag as shown by rocket-powered-model tests at Mach numbers from 0.8 to 1.5

Some effects of body cross-sectional shape, including sunken-canopy design, on drag as shown by rocket-powered-model tests at Mach numbers from 0.8 to 1.5

Date: July 1, 1952
Creator: Stoney, William E , Jr & Putland, Leonard W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of changing solidity by varying the number of blades on performance of an axial flow compressor stage

Some effects of changing solidity by varying the number of blades on performance of an axial flow compressor stage

Date: April 14, 1952
Creator: Standahar, Raymond M & Serovy, George K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of chordwise fences on the aerodynamic characteristics of four moderately sweptback wings in the low-lift range at transonic Mach numbers and at Mach number 1.9

Some effects of chordwise fences on the aerodynamic characteristics of four moderately sweptback wings in the low-lift range at transonic Mach numbers and at Mach number 1.9

Date: July 21, 1950
Creator: Guy, Lawrence D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some Effects of Compressibility on the Flow Through Fans and Turbines

Some Effects of Compressibility on the Flow Through Fans and Turbines

Date: January 1, 1946
Creator: Perl, W. & Epstein, H. T.
Description: The laws of conservation of mass, momentum, and energy are applied to the compressible flow through a two-dimensional cascade of airfoils. A fundamental relation between the ultimate upstream and downstream flow angles, the inlet Mach number, and the pressure ratio across the cascade is derived. Comparison with the corresponding relation for incompressible flow shows large differences. The fundamental relation reveals two ranges of flow angles and inlet Mach numbers, for which no ideal pressure ratio exists. One of these nonideal operating ranges is analogous to a similar type in incompressible flow. The other is characteristic only of compressible flow. The effect of variable axial-flow area is treated. Some implications of the basic conservation laws in the case of nonideal flow through cascades are discussed.
Contributing Partner: UNT Libraries Government Documents Department
Some effects of configuration variables on store loads at supersonic speeds

Some effects of configuration variables on store loads at supersonic speeds

Date: July 6, 1955
Creator: Smith, Norman F & Carlson, Harry W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of exposure to exhaust-gas streams on emittance and thermoelectric power of bare-wire platinum rhodium - platinum thermocouples

Some effects of exposure to exhaust-gas streams on emittance and thermoelectric power of bare-wire platinum rhodium - platinum thermocouples

Date: August 1, 1954
Creator: Glawe, George E & Shepard, Charles E
Description: Thermocouples were exposed to exhaust gases from the combustion of propane, 72-octane gasoline, and JP-4 fuel. Exposure increased the emissivity of the thermocouple wire, which increased its radiation error. Two methods are presented for determining the emittance of the wires. The emissivity of a clean platinum rhodium-platinum thermocouple was approximately 0.2 in the temperature range investigated, while the emittance of an exposed thermocouple coated with exhaust residue was about 0.5. The exposure caused negligible change in the thermoelectric power of the thermocouples.
Contributing Partner: UNT Libraries Government Documents Department
Some effects of fin leading-edge shape on aerodynamic heating at Mach number 2.0 at a stagnation temperature of about 2,600 R

Some effects of fin leading-edge shape on aerodynamic heating at Mach number 2.0 at a stagnation temperature of about 2,600 R

Date: January 9, 1958
Creator: Bland, William M , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of flow spoilers and of aerodynamic balance on the oscillating hinge moments for a swept fin-rudder combination in a transonic wind tunnel

Some effects of flow spoilers and of aerodynamic balance on the oscillating hinge moments for a swept fin-rudder combination in a transonic wind tunnel

Date: May 28, 1958
Creator: Gibson, F. W.; Herr, R. W. & Osborne, R. S.
Description: Flow spoiler and aerodynamic balance effects on oscillating hinge moments for swept fin-rudder combination in transonic wind tunnel.
Contributing Partner: UNT Libraries Government Documents Department
Some effects of flow spoilers and of aerodynamic balance on the oscillating hinge moments for a swept fin-rudder combination in a transonic wind tunnel

Some effects of flow spoilers and of aerodynamic balance on the oscillating hinge moments for a swept fin-rudder combination in a transonic wind tunnel

Date: May 28, 1958
Creator: Herr, Robert W; Gibson, Frederick W & Osborne, Robert S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of fluid in pylon-mounted tanks on flutter

Some effects of fluid in pylon-mounted tanks on flutter

Date: July 19, 1955
Creator: Reese, James R
Description: None
Contributing Partner: UNT Libraries Government Documents Department