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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
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
Lateral-control investigation on a 37 degree sweptback wing of aspect ratio 6 at a Reynolds number of 6,800,000

Lateral-control investigation on a 37 degree sweptback wing of aspect ratio 6 at a Reynolds number of 6,800,000

Date: January 27, 1949
Creator: Koven, William & Graham, Robert R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of the effects of support interference on the drag of bodies of revolution at a Mach number of 1.5

Experimental investigation of the effects of support interference on the drag of bodies of revolution at a Mach number of 1.5

Date: May 7, 1948
Creator: Perkins, Edward W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A study of several parameters controlling the trajectories of a supersonic antiaircraft missile powered with solid- or liquid-fuel rockets

A study of several parameters controlling the trajectories of a supersonic antiaircraft missile powered with solid- or liquid-fuel rockets

Date: April 24, 1947
Creator: Huntsberger, Ralph F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Drag measurements in flight on the 10-percent-thick and 8-percent-thick wing X-1 airplanes

Drag measurements in flight on the 10-percent-thick and 8-percent-thick wing X-1 airplanes

Date: November 19, 1948
Creator: Gardner, John J
Description: None
Contributing Partner: UNT Libraries Government Documents Department