You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1951
 Serial/Series Title: NACA Technical Notes
 Collection: National Advisory Committee for Aeronautics Collection
The aerodynamic behavior of a harmonically oscillating finite sweptback wing in supersonic flow

The aerodynamic behavior of a harmonically oscillating finite sweptback wing in supersonic flow

Date: October 1, 1951
Creator: Chang, Chieh-Chien
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air forces and moments on triangular and related wings with subsonic leading edges oscillating in supersonic potential flow

Air forces and moments on triangular and related wings with subsonic leading edges oscillating in supersonic potential flow

Date: September 1, 1951
Creator: Watkins, Charles E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of an x-ray absorption method for measurement of high gas temperatures

An analysis of an x-ray absorption method for measurement of high gas temperatures

Date: December 1, 1951
Creator: Weltmann, Ruth N & Kuhns, Perry W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of flow in rotating passage of large radial-inlet centrifugal compressor at tip speed of 700 feet per second

An analysis of flow in rotating passage of large radial-inlet centrifugal compressor at tip speed of 700 feet per second

Date: December 1, 1951
Creator: Prian, Vasily D & Michel, Donald J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of pure-bending flutter of a cantilever swept wing and its relation to bending-torsion flutter

Analysis of pure-bending flutter of a cantilever swept wing and its relation to bending-torsion flutter

Date: September 1, 1951
Creator: Cunningham, H J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analytic determination of the flow behind a symmetrical curved shock

An analytic determination of the flow behind a symmetrical curved shock

Date: October 1, 1951
Creator: Lin, C C & Shen, S F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An Analytical and Experimental Investigation of the Skin Friction of the Turbulent Boundary Layer on a Flat Plate at Supersonic Speeds

An Analytical and Experimental Investigation of the Skin Friction of the Turbulent Boundary Layer on a Flat Plate at Supersonic Speeds

Date: February 1, 1951
Creator: Rubesin, Morris W; Maydew, Randall C & Varga, Steven A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analytical evaluation of aerodynamic characteristics of turbines with nontwisted rotor blades

Analytical evaluation of aerodynamic characteristics of turbines with nontwisted rotor blades

Date: May 1, 1951
Creator: Slivka, William R & Silvern, David H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analytical investigation of effect of high-lift flaps on take-off of light airplanes

An analytical investigation of effect of high-lift flaps on take-off of light airplanes

Date: September 1, 1951
Creator: Weick, Fred E; Flanagan, L E , Jr & Cherry, H H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analytical investigation of fully developed laminar flow in tubes with heat transfer with fluid properties variable along the radius

Analytical investigation of fully developed laminar flow in tubes with heat transfer with fluid properties variable along the radius

Date: July 1, 1951
Creator: Deissler, Robert G
Description: Relations were analytically obtained for the prediction of radial distributions of velocity and temperature for fully developed laminar flow of gases and of liquid metals in tubes with fluid properties variable along the radius. The relations are applicable to both heating and cooling of the fluid. By use of the relations for velocity and temperature distributions, relations were obtained among Nusselt number, friction parameter, and ratio of wall to bulk temperature. The Nusselt number and friction parameter were found to be independent of Reynolds number and Prandtl number. The effects of ratio of wall to bulk temperature on Nusselt number and friction parameter could be eliminated by evaluating the fluid properties at specified temperatures in the fluid.
Contributing Partner: UNT Libraries Government Documents Department
An analytical investigation using aerodynamic limitations of several designs of high stage pressure ratio multistage compressors

An analytical investigation using aerodynamic limitations of several designs of high stage pressure ratio multistage compressors

Date: December 1, 1951
Creator: Voit, Charles H & Thomson, Arthur R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analytical method for determining performance of turbojet-engine tail-pipe heat exchangers

Analytical method for determining performance of turbojet-engine tail-pipe heat exchangers

Date: September 1, 1951
Creator: Behun, Michael & Chandler, Harrison C , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Applicability of the hypersonic similarity rule to pressure distributions which include the effects of rotation for bodies of revolution at zero angle of attack

Applicability of the hypersonic similarity rule to pressure distributions which include the effects of rotation for bodies of revolution at zero angle of attack

Date: June 1, 1951
Creator: Rossow, Vernon J.
Description: The analysis of Technical Note 2250, 1950, is extended to include the effects of flow rotation. It is found that the theoretical pressure distributions over drive cylinders can be related by the hypersonic similarity rule with sufficient accuracy for most engineering purposes. The error introduced into pressure distributions and drag effective cylinders by ignoring the rotation term in the characteristic equations is investigated.
Contributing Partner: UNT Libraries Government Documents Department
Application of response function to calculation of flutter characteristics of a wing carrying concentrated masses

Application of response function to calculation of flutter characteristics of a wing carrying concentrated masses

Date: November 1, 1951
Creator: Serbin, H & Costilow, E L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of the Von Karman momentum theorem to turbulent boundary layers

Application of the Von Karman momentum theorem to turbulent boundary layers

Date: December 1, 1951
Creator: Bidwell, Jerold M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of variational methods to transonic flows with shock waves

Application of variational methods to transonic flows with shock waves

Date: November 1, 1951
Creator: Wang, Chi-Teh & Chou, Pei-Chi
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of x-ray absorption to measurement of small air-density gradients

Application of x-ray absorption to measurement of small air-density gradients

Date: July 1, 1951
Creator: Weltmann, Ruth N; Fairweather, Steven & Papke, Daryl
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Approximate calculation of turbulent boundary-layer development in compressible flow

Approximate calculation of turbulent boundary-layer development in compressible flow

Date: April 1, 1951
Creator: Tucker, Maurice
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Approximate design method for high-solidity blade elements in compressors and turbines

Approximate design method for high-solidity blade elements in compressors and turbines

Date: July 1, 1951
Creator: Stanitz, John D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Approximate methods for calculating the flow about nonlifting bodies of revolution at high supersonic airspeeds

Approximate methods for calculating the flow about nonlifting bodies of revolution at high supersonic airspeeds

Date: December 1, 1951
Creator: Eggers, A J , Jr & Savin, Raymond C
Description: Explicit expressions are developed which yield the Mach number and pressure distributions on the surfaces of pointed nonlifting bodies of revolution operating at high supersonic airspeeds and at values of the hypersonic similarity parameter (ratio of free-stream Mach number to slenderness ratio) greater than 1. Very simple explicit expressions are obtained for these distributions in the special case of slender bodies. In the case of cones, the analytic solutions accurately define the entire flow field over a wide range of free-stream Mach numbers and apex angles.
Contributing Partner: UNT Libraries Government Documents Department
Automatic control systems satisfying certain general criterions on transient behavior

Automatic control systems satisfying certain general criterions on transient behavior

Date: June 1, 1951
Creator: Boksenbom, Aaron S & Hood, Richard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Axial-momentum theory for propellers in compressible flow

Axial-momentum theory for propellers in compressible flow

Date: July 1, 1951
Creator: Vogeley, Arthur William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Bench-test investigation of the transient-response characteristics of several simulated airplanes incorporating an autopilot sensitive to yawing accelerations

Bench-test investigation of the transient-response characteristics of several simulated airplanes incorporating an autopilot sensitive to yawing accelerations

Date: July 1, 1951
Creator: Howard, Donald A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A biharmonic relaxation method for calculating thermal stress in cooled irregular cylinders

A biharmonic relaxation method for calculating thermal stress in cooled irregular cylinders

Date: August 1, 1951
Creator: Holms, Arthur G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
FIRST PREV 1 2 3 4 5 NEXT LAST