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 Collection: National Advisory Committee for Aeronautics Collection
Design and experimental performance of a 0.35 hub-tip radius ratio transonic axial-flow-compressor rotor designed for 40 pounds per second per unit frontal area

Design and experimental performance of a 0.35 hub-tip radius ratio transonic axial-flow-compressor rotor designed for 40 pounds per second per unit frontal area

Date: September 4, 1958
Creator: Montgomery, John C & Yasaki, Paul T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Thermal reaction of diborane with trimethylborane

Thermal reaction of diborane with trimethylborane

Date: September 4, 1958
Creator: Lamneck, John H , Jr & Kaye, Samuel
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An Analysis of Ramjet Engines Using Supersonic Combustion

An Analysis of Ramjet Engines Using Supersonic Combustion

Date: September 1, 1958
Creator: Weber, Richard J & Mackay, John S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of the creep behavior of a square plate loaded in edge compression

Analysis of the creep behavior of a square plate loaded in edge compression

Date: September 1, 1958
Creator: Mccomb, Harvey G , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of turbulent flow and heat transfer in noncircular passages

Analysis of turbulent flow and heat transfer in noncircular passages

Date: September 1, 1958
Creator: Deissler, Robert G & Taylor, Maynard F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analytical and experimental investigation of temperature recovery factors for fully developed flow of air in a tube

Analytical and experimental investigation of temperature recovery factors for fully developed flow of air in a tube

Date: September 1, 1958
Creator: Weiland, W F; Lowdermilk, W H & Deissler, R G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analytical study of turbulent and molecular mixing in rocket combustion

An analytical study of turbulent and molecular mixing in rocket combustion

Date: September 1, 1958
Creator: Bittker, David A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of the Method of Coordinate Perturbation to Unsteady Duct Flow

Application of the Method of Coordinate Perturbation to Unsteady Duct Flow

Date: September 1, 1958
Creator: Himmel, Seymour C.
Description: The method of coordinate perturbation is applied to the unsteady flow of a compressible fluid in ducts of variable cross section. Solutions, in the form of perturbation series, are obtained for unsteady flows in ducts for which the logarithmic derivative of area variation with respect to the space coordinate is a function of the 'smallness' parameter of the perturbation series. This technique is applied to the problem of the interaction of a disturbance and a shock wave in a diffuser flow. It is found that, for a special choice of the function describing the disturbance, the path of the shock wave can be expressed in closed form to first order. The method is then applied to the determination of the flow field behind a shock wave moving on a prescribed path in the x,t-plane. Perturbation series solutions for quite general paths are developed. The perturbation series solutions are compared with the more exact solutions obtained by the application of the method of characteristics. The approximate solutions are shown to be in reasonably accurate agreement with the solutions obtained by the method of characteristics.
Contributing Partner: UNT Libraries Government Documents Department
An approach to the problem of estimating severe and repeated gust    loads for missile operations

An approach to the problem of estimating severe and repeated gust loads for missile operations

Date: September 1, 1958
Creator: Press, Harry & Steiner, Roy
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Approximate method for calculating motions in angles of attack and sideslip due to step pitching- and yawing-moment inputs during steady roll

Approximate method for calculating motions in angles of attack and sideslip due to step pitching- and yawing-moment inputs during steady roll

Date: September 1, 1958
Creator: Moul, Martin T & Brennan, Teresa R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Approximate method for calculation of laminar boundary layer with heat transfer on a cone at large angle of attack in supersonic flow

Approximate method for calculation of laminar boundary layer with heat transfer on a cone at large angle of attack in supersonic flow

Date: September 1, 1958
Creator: Brunk, William E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Approximate solutions of a class of similarity equations for three-dimensional, laminar, incompressible boundary-layer flows

Approximate solutions of a class of similarity equations for three-dimensional, laminar, incompressible boundary-layer flows

Date: September 1, 1958
Creator: Hansen, Arthur G & Herzig, Howard Z
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of shock-expansion theory with experiment for the lift, drag, and pitching-moment characteristics of two wing-body combinations at M=5.0

Comparison of shock-expansion theory with experiment for the lift, drag, and pitching-moment characteristics of two wing-body combinations at M=5.0

Date: September 1, 1958
Creator: Savin, Raymond C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A cooled-gas pyrometer for use in high-temperature gas streams

A cooled-gas pyrometer for use in high-temperature gas streams

Date: September 1, 1958
Creator: Krause, Lloyd N; Johnson, Robert C & Glawe, George E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cumulative fatigue damage at elevated temperature

Cumulative fatigue damage at elevated temperature

Date: September 1, 1958
Creator: Rey, William K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of advance ratio on flight performance of a modified supersonic propeller

Effect of advance ratio on flight performance of a modified supersonic propeller

Date: September 1, 1958
Creator: Hammack, Jerome B & O'Bryan, Thomas C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of free-stream turbulence on heat transfer from a flat plate

The effect of free-stream turbulence on heat transfer from a flat plate

Date: September 1, 1958
Creator: Sugawara, Sugao; Sato, Takashi; Komatsu, Hiroyasu & Osaka, Hiroichi
Description: Turbulence was generated by using screens, and the turbulence percentage was measured by a hot-wire anemometer both in the boundary layer and the free stream. The local heat-transfer coefficient was measured at 12 locations along the plate for the cases of various turbulence levels. The transition Reynolds number from laminar to turbulent flow decreases as the main-stream turbulence level increases. In the range of laminar heat transfer the effect of turbulence in the main flow was not great, but in the range of turbulent heat transfer the heat-transfer coefficient increases according to the increase of turbulence.
Contributing Partner: UNT Libraries Government Documents Department
Effect of precipitate particles on creep of aluminum-copper alloys during age hardening

Effect of precipitate particles on creep of aluminum-copper alloys during age hardening

Date: September 1, 1958
Creator: Underwood, E E; Marsh, L L & Manning, G K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of pressure and duct geometry on bluff-body flame stabilization

Effect of pressure and duct geometry on bluff-body flame stabilization

Date: September 1, 1958
Creator: Potter, Andrew E , Jr & Wong, Edgar L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of some external crosswise stiffeners on the heat transfer and pressure distribution on a flat plate at Mach numbers of 0.77, 1.39, and 1.98

Effect of some external crosswise stiffeners on the heat transfer and pressure distribution on a flat plate at Mach numbers of 0.77, 1.39, and 1.98

Date: September 1, 1958
Creator: Carter, Howard S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of compressibility on rotor hovering performance and synthesized blade-section characteristics derived from measured rotor performance of blades having NACA 0015 airfoil tip sections

Effects of compressibility on rotor hovering performance and synthesized blade-section characteristics derived from measured rotor performance of blades having NACA 0015 airfoil tip sections

Date: September 1, 1958
Creator: Shivers, James P & Carpenter, Paul J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of frequency and amplitude on the yawing derivatives of triangular, swept, and unswept wings and of a triangular-wing-fuselage combination with and without a triangular tail performing sinusoidal yawing oscillations

Effects of frequency and amplitude on the yawing derivatives of triangular, swept, and unswept wings and of a triangular-wing-fuselage combination with and without a triangular tail performing sinusoidal yawing oscillations

Date: September 1, 1958
Creator: Letko, William & Fletcher, Herman S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of ground proximity on the thrust of a simple downward-directed jet beneath a flat surface

Effects of ground proximity on the thrust of a simple downward-directed jet beneath a flat surface

Date: September 1, 1958
Creator: Spreemann, Kenneth P & Sherman, Irving R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of nose angle and Mach number on transition on cones at supersonic speeds

Effects of nose angle and Mach number on transition on cones at supersonic speeds

Date: September 1, 1958
Creator: Czarnecki, K R & Jackson, Mary W
Description: An investigation has been made to determine the transition characteristics of a group of smooth, sharp-nosed cones varying from 10 degrees to sixty degrees in included apex angle over a Mach number range from 1.61 to 2.20 and a range of Reynolds number per foot from about 1.5 x 10 to the 6th power to 8 x 10 to the 6th power. Increasing the cone angle is shown to decrease slightly the transition Reynolds number, whereas the effects of changes of Mach number and unit Reynolds number are negligible. When transition occurred within 15 to 20 percent of the model length from the base there was a dropoff in transition Reynolds number. (author).
Contributing Partner: UNT Libraries Government Documents Department