You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
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
Some effects of propeller operation on the distribution of the load on the vertical tail surface of a typical pursuit airplane

Some effects of propeller operation on the distribution of the load on the vertical tail surface of a typical pursuit airplane

Date: March 1, 1944
Creator: Dingeldein, Richard C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of rainfall on flight of airplanes and on instrument indications

Some effects of rainfall on flight of airplanes and on instrument indications

Date: April 1, 1941
Creator: Rhode, Richard V
Description: Several possible effects of heavy rain on the aerodynamic performance of an airplane and of heavy rain and associated atmospheric phenomena on the indications of flight instruments are briefly considered. It is concluded that the effects of heavy rain on the performance of an airplane are not so great as to force the airplane down from moderate altitudes. Serious malfunctioning of the air-speed indicator may occur, however, as a result of flooding of the pitot-static head and subsequent accumulation of water in the air-speed pressure line. In strong convective situations, like thunderstorms, the rate-of-climb indicator may also be seriously in error owing to rapid variations of atmospheric pressure when entering and emerging from the convection currents.
Contributing Partner: UNT Libraries Government Documents Department
Some Effects of Rapid Inlet Pressure Oscillation on the Operation of a Turbojet Engine

Some Effects of Rapid Inlet Pressure Oscillation on the Operation of a Turbojet Engine

Date: January 1, 1958
Creator: Russey, Robert E. & Lubick, Robert J.
Description: A program was conducted in an altitude facility at the NACA Lewis laboratory to investigate the effects of rapid inlet pressure oscillations on the operation of a current turbo jet engine. These pressure oscillations were approximately sinusoidal in form and were generated to cover a frequency range of 2 to 75 cycles per second and an amplitude range of 10 to 70 percent of the free-stream total pressure. As the oscillation progressed through the compressor, the amplitude was attenuated considerably and a relatively large phase shift (lag) occurred. Engine stall limits obtained during pressure oscillations differed from quasi-steady-state stall limits as defined by over-all compressor pressure ratio.
Contributing Partner: UNT Libraries Government Documents Department
Some effects of Reynolds and Mach numbers on the lift of an NACA 0012 rectangular wing in the NACA 19-foot pressure tunnel

Some effects of Reynolds and Mach numbers on the lift of an NACA 0012 rectangular wing in the NACA 19-foot pressure tunnel

Date: May 1, 1943
Creator: Muse, Thomas C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of Reynolds number on the stability of a series of flared-body and blunted-cone models at Mach numbers form 1.62 to 6.86

Some effects of Reynolds number on the stability of a series of flared-body and blunted-cone models at Mach numbers form 1.62 to 6.86

Date: January 7, 1958
Creator: Kehlet, Alan B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of Reynolds number on the stability of a series of flared-body and blunted-cone models at Mach numbers from 1.62 to 6.86

Some effects of Reynolds number on the stability of a series of flared-body and blunted-cone models at Mach numbers from 1.62 to 6.86

Date: January 7, 1958
Creator: Kehlet, A. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of roll rate on the longitudinal stability characteristics of a cruciform missile configuration as determined from flight test for a Mach number range of 1.1 to 1.8

Some effects of roll rate on the longitudinal stability characteristics of a cruciform missile configuration as determined from flight test for a Mach number range of 1.1 to 1.8

Date: June 19, 1956
Creator: Barber, H. T., Jr. & Lundstrom, R. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of roll rate on the longitudinal stability characteristics of a cruciform missile configuration as determined from flight test for a Mach number range of 1.1. to 1.8

Some effects of roll rate on the longitudinal stability characteristics of a cruciform missile configuration as determined from flight test for a Mach number range of 1.1. to 1.8

Date: June 19, 1956
Creator: Lundstrom, Reginald R & Baber, Hal T , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some Effects of Roll Rate on the Longitudinal Stability Characteristics of the Hughes Falcon Missile, ''C'' Configuration, for a Mach Number Range of 1.1 to 1.8 as Determined from Flight Test

Some Effects of Roll Rate on the Longitudinal Stability Characteristics of the Hughes Falcon Missile, ''C'' Configuration, for a Mach Number Range of 1.1 to 1.8 as Determined from Flight Test

Date: December 27, 1955
Creator: Baber, H. T., Jr. & Lundstrom, R. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of roughness on stagnation-point heat transfer at a Mach number of 2, a stagnation temperature of 3,530 F, and a Reynolds number of 2.5 x 10(exp 6) per foot

Some effects of roughness on stagnation-point heat transfer at a Mach number of 2, a stagnation temperature of 3,530 F, and a Reynolds number of 2.5 x 10(exp 6) per foot

Date: May 26, 1958
Creator: Strass, H Kurt & Tyner, Thomas W
Description: None
Contributing Partner: UNT Libraries Government Documents Department