You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Collection: National Advisory Committee for Aeronautics Collection
Results 13311 - 13334 of 13,806
  |   |  
Effect of jet temperature on jet-noise generation

Effect of jet temperature on jet-noise generation

Date: March 1, 1958
Creator: Rollin, Vern G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of overheating on creep-rupture properties of M-252 alloy

Effect of overheating on creep-rupture properties of M-252 alloy

Date: March 1, 1958
Creator: Rowe, John P & Freeman, J W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of wall cooling on inlet parameters of a scoop operating in a turbulent boundary layer on a flat or conical surface for Mach numbers 2 to 10

Effect of wall cooling on inlet parameters of a scoop operating in a turbulent boundary layer on a flat or conical surface for Mach numbers 2 to 10

Date: March 1, 1958
Creator: Beke, Andrew
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Interaction of a Reflected Shock Wave with the Boundary Layer in a Shock Tube

The Interaction of a Reflected Shock Wave with the Boundary Layer in a Shock Tube

Date: March 1, 1958
Creator: Mark, Herman
Description: Ideally, the reflection of a shock from the closed end of a shock tube provides, for laboratory study, a quantity of stationary gas at extremely high temperature. Because of the action of viscosity, however, the flow in the real case is not one-dimensional, and a boundary layer grows in the fluid following the initial shock wave. In this paper simplifying assumptions are made to allow an analysis of the interaction of the shock reflected from the closed end with the boundary layer of the initial shock afterflow. The analysis predicts that interactions of several different types will exist in different ranges of initial shock Mach number. It is shown that the cooling effect of the wall on the afterflow boundary layer accounts for the change in interaction type. An experiment is carried out which verifies the existence of the several interaction regions and shows that they are satisfactorily predicted by the theory. Along with these results, sufficient information is obtained from the experiments to make possible a model for the interaction in the most complicated case. This model is further verified by measurements made during the experiment. The case of interaction with a turbulent boundary layer is also considered. Identifying ...
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Aperiodic Time Processes with Autocorrelation and Fourier Analysis

Investigation of Aperiodic Time Processes with Autocorrelation and Fourier Analysis

Date: March 1, 1958
Creator: Exner, Marie Luise
Description: Autocorrelation and frequency analyses of a series of aperiodic time events, in particular, filtered noises and sibilant sounds, were made. The position and band width of the frequency ranges are best obtained from the frequency analysis, but the energies contained in the several bands are most easily obtained from the autocorrelation function. The mean number of zero crossings of the time function was determined from the curvature of the latter function in the vicinity of the zero crossing, and also with the aid of a decimal counter. The second method was found to be more exact.
Contributing Partner: UNT Libraries Government Documents Department
Measurements of total hemispherical emissivity of various oxidized metals at high temperature

Measurements of total hemispherical emissivity of various oxidized metals at high temperature

Date: March 1, 1958
Creator: Wade, William R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A method for the calculation of wave drag on supersonic-edged wings and biplanes

A method for the calculation of wave drag on supersonic-edged wings and biplanes

Date: March 1, 1958
Creator: Lomax, Harvard & Sluder, Loma
Description: None
Contributing Partner: UNT Libraries Government Documents Department
NACA Conference on high-speed aerodynamics

NACA Conference on high-speed aerodynamics

Date: March 1, 1958
Creator: unknown
Description: This document contains reproductions of technical papers presented by staff members of the NACA Laboratories at the NACA Conference on High-Speed Aerodynamics held at the Ames Aeronautical Laboratory of the NACA, March 18, 19, and 20, 1958. The primary purpose of this conference was to convey to the military services and their contractors the results of recent research results and to provide those attending an opportunity to discuss the results. The papers in this document were prepared for presentation at the conference and are considered as complementary to, rather than as substitutes for, the Committee's more complete and formal reports.
Contributing Partner: UNT Libraries Government Documents Department
Prandtl-Meyer expansion of chemically reacting gases in local chemical and thermodynamic equilibrium

Prandtl-Meyer expansion of chemically reacting gases in local chemical and thermodynamic equilibrium

Date: March 1, 1958
Creator: Heims, Steve P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Pressure distributions at transonic speeds for parabolic-arc bodies of revolution having fineness ratios of 10, 12, and 14

Pressure distributions at transonic speeds for parabolic-arc bodies of revolution having fineness ratios of 10, 12, and 14

Date: March 1, 1958
Creator: Taylor, Robert A & Mcdevitt, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Propellant vaporization as a criterion for rocket engine design : relation between percentage of propellant vaporized and engine performance

Propellant vaporization as a criterion for rocket engine design : relation between percentage of propellant vaporized and engine performance

Date: March 1, 1958
Creator: Heidmann, Marcus F & Priem, Richard J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Skin-friction measurements in incompressible flow

Skin-friction measurements in incompressible flow

Date: March 1, 1958
Creator: Smith, Donald W & Walker, John H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Transient heating effects on the bending strength of integral aluminum-alloy box beams

Transient heating effects on the bending strength of integral aluminum-alloy box beams

Date: March 1, 1958
Creator: Pride, Richard A & Hall, John B , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wall pressure fluctuations in a turbulent boundary layer

Wall pressure fluctuations in a turbulent boundary layer

Date: March 1, 1958
Creator: Willmarth, William W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Static longitudinal and lateral stability and control characteristics of a model of a swept-wing fighter-bomber-type airplane with a top inlet at Mach numbers from 1.6 to 2.35

Static longitudinal and lateral stability and control characteristics of a model of a swept-wing fighter-bomber-type airplane with a top inlet at Mach numbers from 1.6 to 2.35

Date: March 3, 1958
Creator: Gnos, A Vernon & Kurkowski, Richard L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Summary of locations, extents, and intensities of turbulent areas encountered during flight investigations of the jet stream from January 7, 1957 to April 28, 1957

Summary of locations, extents, and intensities of turbulent areas encountered during flight investigations of the jet stream from January 7, 1957 to April 28, 1957

Date: March 3, 1958
Creator: Copp, Martin R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of a hot-jet exhaust on pressure distributions and external drag of several afterbodies on a single-engine airplane model at transonic speeds

Effect of a hot-jet exhaust on pressure distributions and external drag of several afterbodies on a single-engine airplane model at transonic speeds

Date: March 4, 1958
Creator: Norton, Harry T , Jr & Swihart, John M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effects of a modified roll-command system on the flight-path stability and tracking accuracy of an automatic interceptor

The effects of a modified roll-command system on the flight-path stability and tracking accuracy of an automatic interceptor

Date: March 4, 1958
Creator: Triplett, William C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Study of exit phase of flight of a very high altitude hypersonic airplane by means of a pilot-controlled analog computer

Study of exit phase of flight of a very high altitude hypersonic airplane by means of a pilot-controlled analog computer

Date: March 4, 1958
Creator: Sherman, Windsor L; Faber, Stanley & Whitten, James B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of surface roughness and extreme cooling on boundary-layer transition for 15 deg cone-cylinder in free flight at Mach numbers to 7.6

Effects of surface roughness and extreme cooling on boundary-layer transition for 15 deg cone-cylinder in free flight at Mach numbers to 7.6

Date: March 5, 1958
Creator: Rabb, L. & Krasnican, M. J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of the effect of circumferential inlet flow distortion on the performance of a five-stage axial-flow research compressor with transonic rotors in all stages

Experimental investigation of the effect of circumferential inlet flow distortion on the performance of a five-stage axial-flow research compressor with transonic rotors in all stages

Date: March 5, 1958
Creator: Robbins, William H & Glaser, Frederick
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of a two-dimensional cascade inlet at a free-stream Mach number of 3.05 and at angles of attack of -3 degrees, 0 degrees, 3 degrees, and 6 degrees

Performance of a two-dimensional cascade inlet at a free-stream Mach number of 3.05 and at angles of attack of -3 degrees, 0 degrees, 3 degrees, and 6 degrees

Date: March 5, 1958
Creator: Woolett, Richard R & Ferguson, Harold M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of canard surface size on stability and control characteristics of two canard airplane configuration at Mach numbers of 1.41 and 2.01

Effects of canard surface size on stability and control characteristics of two canard airplane configuration at Mach numbers of 1.41 and 2.01

Date: March 6, 1958
Creator: Spearman, M Leroy & Driver, Cornelius
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of a high-flow transonic-compressor inlet stage having a hub-tip radius of 0.35

Investigation of a high-flow transonic-compressor inlet stage having a hub-tip radius of 0.35

Date: March 6, 1958
Creator: Felix, A Richard
Description: None
Contributing Partner: UNT Libraries Government Documents Department