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  Partner: UNT Libraries Government Documents Department
 Resource Type: Report
 Decade: 1950-1959
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 RADIATION ON SOLVENT EXTRACTION PROCESSES

SOME EFFECTS OF RADIATION ON SOLVENT EXTRACTION PROCESSES

Date: January 26, 1959
Creator: Davis, W. Jr. & Wagner, R.M.
Description: The yield of total acid, G/sub acid/, in the radiolysis of tributyl phosphate-Amsco 125-82 solutions is 2.7 times the electron fraction of TBP, or approximately 2.7 times the weight fraction of TBP, per 100 ev of energy absorbed by the solution. Dibutyl phosphoric acid, DBPA, constitutes about 85% of the acid. Radiolysis of TBP also results in the conversion of abcut 0.9 molecules of TBP to a polymer per 100 ev of energy absorbed. Uranium extraction-stripping tests with an 8 stage spinner column have shown that one mole of uranium is retained in the organic phase during the stripping operation per mole of DBPA added pnior to the extraction operation. On the basis of a tentative molecular weight of 848 g/mole, the polymer retains in the organic phase during stripping operations about 1.2 moles of uranium per mole of polymer added prior to extraction. In addition to polymer and acids, condensed phase radiolysis prcducts include olefins, whose yield, expressed as G/sub c=c/, or number of double bonds formed per 100 ev of energy absorbed, decreases from ca 4 to 1 as the TBP concentration increases from 4.5 to 100 wt.%. Diethyl carbcnate (DEC) was tested for uranium retention and fission ...
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 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
Some effects of side-wall modifications on the drag and pressure recovery of an NACA submerged inlet at transonic speeds

Some effects of side-wall modifications on the drag and pressure recovery of an NACA submerged inlet at transonic speeds

Date: February 15, 1952
Creator: Taylor, Robert A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of small-scale flow disturbance on nozzle-burner flames

Some effects of small-scale flow disturbance on nozzle-burner flames

Date: September 1, 1956
Creator: Wong, Edgar L
Description: Laminar-like and brush-like propane-air flames were obtained when wire grids were used as turbulence generators in a 1/2-inch nozzle burner. The laminar-like flames for grid-disturbed flow had a slightly higher burning velocity than "true" laminar flames (no grid used). The brush-like flames were similar to those obtained with pipe turbulent flow. Their burning-velocity dependence on a "flow disturbance" Reynolds number compared favorably with that obtained for pipe turbulent flames. Hot-wire-anemometer equipment was used to measure the flow disturbance intensity in the cold flow with and without the grids in place.
Contributing Partner: UNT Libraries Government Documents Department
Some effects of solidity on turning through constant-thickness circular-arc guide vanes in axial annular flow

Some effects of solidity on turning through constant-thickness circular-arc guide vanes in axial annular flow

Date: August 24, 1951
Creator: Mankuta, Harry & Guentert, Donald C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of spanwise aileron location and wing structural rigidity on the rolling effectiveness of 0.3-chord flap-type ailerons on a tapered wing having 63 degrees sweepback at the leading edge and NACA 64A005 airfoil sections

Some effects of spanwise aileron location and wing structural rigidity on the rolling effectiveness of 0.3-chord flap-type ailerons on a tapered wing having 63 degrees sweepback at the leading edge and NACA 64A005 airfoil sections

Date: June 22, 1951
Creator: Strass, H Kurt; Fields, E M & Schult, Eugene D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of spoiler height, wing flexibility, and wing thickness on rolling effectiveness and drag of unswept wings at Mach numbers between 0.4 and 1.7

Some effects of spoiler height, wing flexibility, and wing thickness on rolling effectiveness and drag of unswept wings at Mach numbers between 0.4 and 1.7

Date: October 7, 1952
Creator: Fields, E M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of sweep and aspect ratio on the transonic flutter characteristics of a series of thin cantilever wings having a taper ratio of 0.6

Some effects of sweep and aspect ratio on the transonic flutter characteristics of a series of thin cantilever wings having a taper ratio of 0.6

Date: January 24, 1956
Creator: Unangst, John R & Jones, George W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of sweep and thickness on the experimental downwash characteristics at transonic speeds of a series of highly tapered wings with an aspect ratio of 3 : transonic bump method

Some effects of sweep and thickness on the experimental downwash characteristics at transonic speeds of a series of highly tapered wings with an aspect ratio of 3 : transonic bump method

Date: February 16, 1956
Creator: Few, Albert G , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of system nonlinearities in the problem of aircraft flutter

Some effects of system nonlinearities in the problem of aircraft flutter

Date: October 1, 1955
Creator: Woolston, Donald S; Runyan, Harry L & Byrdsong, Thomas A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of tail height and wing plan form on the static longitudinal stability characteristics of a small-scale model at high subsonic speeds

Some effects of tail height and wing plan form on the static longitudinal stability characteristics of a small-scale model at high subsonic speeds

Date: May 1, 1957
Creator: Few, Albert G , Jr & King, Thomas J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of valve friction and shock stick friction on control quality in a helicopter with hydraulic-power control systems

Some effects of valve friction and shock stick friction on control quality in a helicopter with hydraulic-power control systems

Date: May 1, 1957
Creator: Brown, B Porter & REEDER JOHN P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of vanes and of turbulence in two-dimensional wide-angle subsonic diffusers

Some effects of vanes and of turbulence in two-dimensional wide-angle subsonic diffusers

Date: June 1, 1958
Creator: Moore, Carl A , Jr & Kline, Stephen J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of variations in several parameters including fluid density on the flutter speed of light uniform cantilever wings

Some effects of variations in several parameters including fluid density on the flutter speed of light uniform cantilever wings

Date: December 1, 1951
Creator: Woolston, Donald S & Castile, George E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of varying the damping in pitch and roll on the flying qualities of a small single-rotor helicopter

Some effects of varying the damping in pitch and roll on the flying qualities of a small single-rotor helicopter

Date: January 1, 1952
Creator: Reeder, John P & Whitten, James B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of wing fences on the lateral stability derivatives of a 60 degree delta wing oscillating continuously in yaw

Some effects of wing fences on the lateral stability derivatives of a 60 degree delta wing oscillating continuously in yaw

Date: July 11, 1956
Creator: Riley, Donald R
Description: None
Contributing Partner: UNT Libraries Government Documents Department