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 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
Some effects of frequency on the contribution of a vertical tail to the free aerodynamic damping of a model oscillating in yaw

Some effects of frequency on the contribution of a vertical tail to the free aerodynamic damping of a model oscillating in yaw

Date: January 1, 1953
Creator: Bird, John D; Fisher, Lewis R & Hubbard, Sadie M
Description: The damping in yaw and the directional stability of a model freely oscillating in yaw were measured tail-off and tail-on and compared with the values obtained by theoretical consideration of the unsteady lift associated with an oscillating vertical tail. A range of low frequencies comparable to those of the lateral motions of airplanes was covered. The analysis includes the effects of vertical-tail aspect ratio and the two-dimensional effects of compressibility.
Contributing Partner: UNT Libraries Government Documents Department
Some effects of fuselage flexibility on longitudinal stability and control

Some effects of fuselage flexibility on longitudinal stability and control

Date: April 1, 1956
Creator: Klawans, Bernard B & Johnson, Harold I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of fuselage interference, wing interference, and sweepback on the damping in roll of untapered wings as determined by techniques employing rocket-propelled vehicles

Some effects of fuselage interference, wing interference, and sweepback on the damping in roll of untapered wings as determined by techniques employing rocket-propelled vehicles

Date: October 8, 1951
Creator: Bland, William M , Jr & Dietz, Albert E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of guide-vane turning and stators on the rotating stall characteristics of a high hub-tip ratio single-stage compressor

Some effects of guide-vane turning and stators on the rotating stall characteristics of a high hub-tip ratio single-stage compressor

Date: April 1, 1956
Creator: Costilow, Eleanor L & Huppert, Merle C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of gutter flame-holder dimensions on combustion-chamber performance of 20-inch ram jet

Some effects of gutter flame-holder dimensions on combustion-chamber performance of 20-inch ram jet

Date: July 30, 1948
Creator: Perchonok, Eugene; Wishnek, George & Wilcox, Fred A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of heat transfer at Mach number 2.0 at stagnation temperatures between 2,310 and 3,500 R on a magnesium fin with several leading-edge modifications

Some effects of heat transfer at Mach number 2.0 at stagnation temperatures between 2,310 and 3,500 R on a magnesium fin with several leading-edge modifications

Date: April 18, 1957
Creator: Bland, William M , Jr & Bressette, Walter E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of injection advance angle, engine-jacket temperature, and speed on combustion in a compression-ignition engine

Some effects of injection advance angle, engine-jacket temperature, and speed on combustion in a compression-ignition engine

Date: January 1, 1936
Creator: Rothrock, A M & Waldron, C D
Description: An optical indicator and a high-speed motion-picture camera capable of operating at the rate of 2,000 frames per second were used to record simultaneously the pressure development and the flame formation in the combustion chamber of the NACA combustion apparatus. Tests were made at engine speeds of 570 and 1,500 r.p.m. The engine-jacket temperature was varied from 100 degrees to 300 degrees F. And the injection advance angle from 13 degrees after top center to 120 degrees before top center. The results show that the course of the combustion is largely controlled by the temperature and pressure of the air in the chamber from the time the fuel is injected until the time at which combustion starts and by the ignition lag. The conclusion is presented that in a compression-ignition engine with a quiescent combustion chamber the ignition lag should be the longest that can be used without excessive rates of pressure rise; any further shortening of the ignition lag decreased the effective combustion of the engine.
Contributing Partner: UNT Libraries Government Documents Department
Some effects of internal coolants on knock-limited and temperature-limited power as determined in a single-cylinder aircraft test engine

Some effects of internal coolants on knock-limited and temperature-limited power as determined in a single-cylinder aircraft test engine

Date: August 1, 1944
Creator: Slough, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of joint conductivity on the temperatures and thermal stresses in aerodynamically heated skin-stiffener combinations

Some effects of joint conductivity on the temperatures and thermal stresses in aerodynamically heated skin-stiffener combinations

Date: June 1, 1956
Creator: Griffith, George E & Miltonberger, Georgene H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of leading-edge roughness on the aileron effectiveness and drag of a thin rectangular wing employing a full-span plain aileron at Mach numbers from 0.6 to 1.5

Some effects of leading-edge roughness on the aileron effectiveness and drag of a thin rectangular wing employing a full-span plain aileron at Mach numbers from 0.6 to 1.5

Date: November 4, 1953
Creator: English, Roland D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of mass ratio on the transonic flutter characteristics of untapered 45 degree sweptback wings of aspect ratios 2 and 3.5

Some effects of mass ratio on the transonic flutter characteristics of untapered 45 degree sweptback wings of aspect ratios 2 and 3.5

Date: June 24, 1958
Creator: Kelly, H Neale
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of nonlinear variation in the directional-stability and damping-in-yawing derivatives on the lateral stability of an airplane

Some effects of nonlinear variation in the directional-stability and damping-in-yawing derivatives on the lateral stability of an airplane

Date: January 1, 1951
Creator: Sternfield, Leonard
Description: A theoretical investigation has been made to determine the effect of nonlinear stability derivatives on the lateral stability of an airplane. Motions were calculated on the assumption that the directional-stability and the damping-in-yawing derivatives are functions of the angle of sideslip. The application of the Laplace transform to the calculation of an airplane motion when certain types of nonlinear derivatives are present is described in detail. The types of nonlinearities assumed correspond to the condition in which the values of the directional-stability and damping-in-yawing derivatives are zero for small angle of sideslip.
Contributing Partner: UNT Libraries Government Documents Department
Some effects of nonlinear variation in the directional-stability and damping-in-yawing derivatives on the lateral stability of an airplane

Some effects of nonlinear variation in the directional-stability and damping-in-yawing derivatives on the lateral stability of an airplane

Date: November 1, 1950
Creator: Sternfield, Leonard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of propeller operation and location on ability of a wing with plain flaps to deflect propeller slipstreams downward for vertical take-off

Some effects of propeller operation and location on ability of a wing with plain flaps to deflect propeller slipstreams downward for vertical take-off

Date: January 1, 1955
Creator: Draper, John W & Kuhn, Richard E
Description: None
Contributing Partner: UNT Libraries Government Documents Department