You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Ice protection of turbojet engines by inertia separation of water III : annular submerged inlets

Ice protection of turbojet engines by inertia separation of water III : annular submerged inlets

Date: June 8, 1948
Creator: Von Glahn, Uwe
Description: Aerodynamic and icing studies were conducted on a one-half-scale model of an annular submerged inlet for use with axial-flow turbojet engines. Pressure recoveries, screen radial-velocity profiles, circumferential mass-flow variations, and icing characteristics were determined at the compressor inlet. In order to be effective in maintaining water-free induction air, the inlet gap must be extremely small and ram-pressure recoveries consequently are low, the highest achieved being 65 percent at inlet-velocity ratio of 0.86. All inlets exhibited considerable screen icing. Severe mass-flow shifts occurred at angles of attack.
Contributing Partner: UNT Libraries Government Documents Department
Limited measurements of static longitudinal stability in flight of Douglas D-558-1 airplane (BuAero No. 37971)

Limited measurements of static longitudinal stability in flight of Douglas D-558-1 airplane (BuAero No. 37971)

Date: June 24, 1948
Creator: Williams, Walter C
Description: Contains a few measurements of the variation of elevator angle and elevator force with Mach number at 30,000 feet altitude up to a Mach number of 0.85. These data show that the airplane possessed positive static longitudinal stability up to a Mach number of 0.80. A trim change in the nose-down direction occurred for Mach numbers above 0.82.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical performance of some rocket propellants containing hydrogen, nitrogen, and oxygen

Theoretical performance of some rocket propellants containing hydrogen, nitrogen, and oxygen

Date: May 26, 1948
Creator: Miller, Riley O & Ordin, Paul M
Description: Theoretical performance data including nozzle-exit temperature, specific impulse, volume specific impulse and composition, temperature, and mean molecular weight of reaction products based on frozen equilibrium and isentropic expansion are presented for 13 propellant combinations at reaction pressure of 300 pounds per square inch absolute and expansion ratio of 20.4. On basis of maximum specific impulse alone, five fuels had the following order for any given oxidant: liquid hydrogen, hydrazine, liquid ammonia, and either hydrazine hydrate or hydroxylamine. Three oxidants with a given fuel had the following order: liquid ozone, liquid oxygen, and 100-percent hydrogen peroxide.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary investigation of combustion in flowing gas with various turbulence promoters

Preliminary investigation of combustion in flowing gas with various turbulence promoters

Date: June 7, 1948
Creator: Haddock, Gordon W & Childs, J Howard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of Preliminary Flight Tests of the XS-1 Airplane (8-Percent Wing) to a Mach Number of 1.25

Results of Preliminary Flight Tests of the XS-1 Airplane (8-Percent Wing) to a Mach Number of 1.25

Date: April 6, 1948
Creator: Williams, W C & Beeler, De E
Description: Presents results of the U. S. Air Forces' accelerated transonic flight tests of the XS-1 No. 1 airplane for the Mach number range from 0.70 to 1.25 at altitudes from 30,000 to 49,000 feet. Data are included on horizontal-tail loads and buffeting, longitudinal trim changes, elevator effectiveness and control forces, and lateral trim characteristics.
Contributing Partner: UNT Libraries Government Documents Department
Flight tests of a two-dimensional wedge diffuser at transonic and supersonic speeds

Flight tests of a two-dimensional wedge diffuser at transonic and supersonic speeds

Date: August 11, 1948
Creator: Faget, M A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of horn balances on a 45 degree sweptback horizontal tail surface at high subsonic speeds

Investigation of horn balances on a 45 degree sweptback horizontal tail surface at high subsonic speeds

Date: December 3, 1948
Creator: Johnson, Harold S & Thompson, Robert F
Description: A wind-tunnel investigation of horn balances on a 45 degree sweptback, semispan, horizontal tail surface was made to determine the effects of horn size and inboard-edge fairing at a Mach number of 0.30 and to determine the effects of compressibility up to a Mach number of 0.89. Presented are lift, drag, pitching-moment, and hinge-moment data and lift and hinge-moment parameters.
Contributing Partner: UNT Libraries Government Documents Department
Vibration survey of blades in 10-stage axial-flow compressor I : static investigation

Vibration survey of blades in 10-stage axial-flow compressor I : static investigation

Date: January 31, 1949
Creator: Meyer, Andre J , Jr & Calvert, Howard F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Langley free-flight-tunnel investigation of the automatic lateral stability characteristics of a model equipped with a gyro stabilizing unit that provided either flicker-type or hunting control

Langley free-flight-tunnel investigation of the automatic lateral stability characteristics of a model equipped with a gyro stabilizing unit that provided either flicker-type or hunting control

Date: January 11, 1949
Creator: Schade, Robert O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Residual stress analysis of overspeeded disk with central hole by x-ray diffraction

Residual stress analysis of overspeeded disk with central hole by x-ray diffraction

Date: July 23, 1948
Creator: Good, James N
Description: An X-ray - diffraction analysis of residual surface stresses after plastic strain was introduced in a parallel-sided 3S-O aluminum disk with a central hole by two types of centrifugal overspeed is reported. Both tangential and radial stresses were generally tensile with large local variations near the hole where surface stresses may have been partly superficial. These stresses were both tensile and compressive dependent on the distance from the disk center when mass compression was effected near the hole.
Contributing Partner: UNT Libraries Government Documents Department