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 Decade: 1940-1949
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Wind-tunnel investigation of horizontal tails IV : unswept plan form of aspect ratio 2 and a two-dimensional model

Wind-tunnel investigation of horizontal tails IV : unswept plan form of aspect ratio 2 and a two-dimensional model

Date: December 16, 1948
Creator: Dods, Jules B , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of air jets simulating chines or multiple steps on the hydrodynamic characteristics of a streamline fuselage

The effect of air jets simulating chines or multiple steps on the hydrodynamic characteristics of a streamline fuselage

Date: January 7, 1949
Creator: Weinflash, Bernard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation of the rolling effectiveness at high subsonic, transonic, and supersonic speeds of leading-edge and trailing-edge ailerons in conjunction with tapered and untapered plan forms

Free-flight investigation of the rolling effectiveness at high subsonic, transonic, and supersonic speeds of leading-edge and trailing-edge ailerons in conjunction with tapered and untapered plan forms

Date: July 23, 1948
Creator: Strass, H Kurt
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness

Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness

Date: January 12, 1949
Creator: Lockwood, Vernard E; Vogler, Raymond D & Turner, Thomas R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analytical method of estimating turbine performance

An analytical method of estimating turbine performance

Date: December 29, 1948
Creator: Kochendorfer, Fred D & Nettles, J Cary
Description: A method is developed by which the performance of a turbine over a range of operating conditions can be analytically estimated from the blade angles and flow areas. In order to use the method, certain coefficients that determine the weight flow and friction losses must be approximated. The method is used to calculate the performance of the single-stage turbine of a commercial aircraft gas-turbine engine and the calculated performance is compared with the performance indicated by experimental data. For the turbine of the typical example, the assumed pressure losses and turning angles give a calculated performance that represents the trends of the experimental performance with reasonable accuracy. The exact agreement between analytical performance and experimental performance is contingent upon the proper selection of the blading-loss parameter. A variation of blading-loss parameter from 0.3 to 0.5 includes most of the experimental data from the turbine investigated.
Contributing Partner: UNT Libraries Government Documents Department
The subsonic aerodynamic characteristics of two double-wedge airfoil sections suitable for supersonic flight

The subsonic aerodynamic characteristics of two double-wedge airfoil sections suitable for supersonic flight

Date: May 12, 1947
Creator: Solomon, Joseph & Henney, Floyd W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of airfoil profile of symmetrical sections on the low-speed static-stability and yawing derivatives of 45 degrees sweptback wing models of aspect ratio 2.61

Effect of airfoil profile of symmetrical sections on the low-speed static-stability and yawing derivatives of 45 degrees sweptback wing models of aspect ratio 2.61

Date: November 9, 1948
Creator: Letko, William & Jaquet, Byron M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
: The linear perturbation theory of axially symmetric compressible flow with application to the effect of compressibility on the pressure coefficient at the surface of a body of revolution

: The linear perturbation theory of axially symmetric compressible flow with application to the effect of compressibility on the pressure coefficient at the surface of a body of revolution

Date: July 18, 1947
Creator: Herriot, John G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of flying-boat hulls having length-beam ratios of 20 and 30

Aerodynamic characteristics of flying-boat hulls having length-beam ratios of 20 and 30

Date: November 10, 1948
Creator: Riebe, John M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the dynamic lateral stability characteristics of Douglas design No. 39C, an early version of the X-3 research airplane

Theoretical investigation of the dynamic lateral stability characteristics of Douglas design No. 39C, an early version of the X-3 research airplane

Date: January 18, 1949
Creator: Bennett, Charles V
Description: Contains results of calculations made to determine the neutral oscillatory stability boundaries, period and time to damp of the oscillatory mode, and motions following disturbances. The calculations were made for Mach numbers of 0.75 and 2.3 at an attitude of 35,000 feet and for the landing condition at sea level.
Contributing Partner: UNT Libraries Government Documents Department
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