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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
Notes on the effect of surface distortions on the drag and critical Mach number of airfoils

Notes on the effect of surface distortions on the drag and critical Mach number of airfoils

Date: September 1, 1943
Creator: Allen, J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
NACA Investigation of a Jet-Propulsion System Applicable to Flight

NACA Investigation of a Jet-Propulsion System Applicable to Flight

Date: April 1, 1944
Creator: Brown, Clinton E.
Description: Following a brief history of the NACA investigation of jet-propulsion, a discussion is given of the general investigation and analyses leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight-performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made. It was found that the main fire could be restricted to an intense, small, and short annular blue flame burning steadily and under control in the intended combustion space. With these readily obtainable combustion conditions, the combustion chamber the nozzle walls and the surrounding structure could be maintained at normal temperatures. The system investigated was found to be capable of burning one-half the intake air up the fuel rates of 3 pounds per second. Calculations were shown to agree well with experiment. It was concluded that the basic features of the jet-propulsion system investigation in the ground-test mock-up were ...
Contributing Partner: UNT Libraries Government Documents Department
Investigation of flow in an axially symmetrical heated jet of air

Investigation of flow in an axially symmetrical heated jet of air

Date: December 1, 1943
Creator: Corrsin, Stanley
Description: The work done under this contract falls essentially into two parts: the first part was the design and construction of the equipment and the running of preliminary tests on the 3-inch jet, carried out by Mr. Carl Thiele in 1940; the second part consisting in the measurement in the 1-inch jet flow in an axially symmetrical heated jet of air. (author).
Contributing Partner: UNT Libraries Government Documents Department
Physical data on certain alloys for high temperature applications

Physical data on certain alloys for high temperature applications

Date: April 1, 1943
Creator: Rote, F B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
High temperature characteristics of 17 alloys at 1200 and 1350 F

High temperature characteristics of 17 alloys at 1200 and 1350 F

Date: March 1, 1944
Creator: White, A E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Data for Design of Entrance Vanes from Two-Dimensional Tests of Airfoils in Cascade

Data for Design of Entrance Vanes from Two-Dimensional Tests of Airfoils in Cascade

Date: January 1, 1945
Creator: Zimmey, Charles M. & Lappi, Viola M.
Description: As a part of a program of the NACA directed toward increasing the efficiency of compressors and turbines, data were obtained for application to the design of entrance vanes for axfax-flow compressors or turbines. A series of blower-blade sections with relatively high critical speeds have been developed for turning air efficiently from 0 deg to 80 deg starting with an axial direction. Tests were made of five NACA 65-series blower blades (modified NACA 65(216)-010 airfoils) and of four experimentally designed blower blades in a stationary cascade at low Mach numbers. The turning effectiveness and the pressure distributions of these blade sections at various angles of attack were evaluated over a range of solidities near 1. Entrance-vane design charts are presented that give a blade section and angle of attack for any desired turning angle. The blades thus obtained operate with peak-free pressure distributions. Approximate critical Mach numbers were calculated from the pressure distributions.
Contributing Partner: UNT Libraries Government Documents Department
An analytical investigation of the effects of elevator-fabric distortion on the longitudinal stability and control of an airplane

An analytical investigation of the effects of elevator-fabric distortion on the longitudinal stability and control of an airplane

Date: May 1, 1944
Creator: Mathews, Charles W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of tilt of the propeller axis on the longitudinal-stability characteristics of single-engine airplanes

Effect of tilt of the propeller axis on the longitudinal-stability characteristics of single-engine airplanes

Date: January 1, 1944
Creator: Delany, Noel K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Supersonic Axial-Flow Compressor

The Supersonic Axial-Flow Compressor

Date: January 1, 1950
Creator: Kantrowitz, Arthur
Description: An investigation has been made to explore the possibilities of axial-flow compressors operating with supersonic velocities into the blade rows. Preliminary calculations showed that very high pressure ratios across a stage, together with somewhat increased mass flows, were apparently possible with compressors which decelerated air through the speed of sound in their blading. The first phase of the investigation was the development of efficient supersonic diffusers to decelerate air through the speed of sound. The present report is largely a general discussion of some of the essential aerodynamics of single-stage supersonic axial-flow compressors. As an approach to the study of supersonic compressors, three possible velocity diagrams are discussed briefly. Because of the encouraging results of this study, an experimental single-stage supersonic compressor has been constructed and tested in Freon-12. In this compressor, air decelerates through the speed of sound in the rotor blading and enters the stators at subsonic speeds. A pressure ratio of about 1.8 at an efficiency of about 80 percent has been obtained.
Contributing Partner: UNT Libraries Government Documents Department
Determination of the Stability and Control Characteristics of a Tailless All-Wing Airplane Model with Sweepback in the Langley Free-Flight Tunnel

Determination of the Stability and Control Characteristics of a Tailless All-Wing Airplane Model with Sweepback in the Langley Free-Flight Tunnel

Date: February 1, 1945
Creator: Seacord, Charles L. & Campbell, John P.
Description: Force and flight tests were performance on an all-wing model with windmilling propellers. Tests were conducted with deflected and retracted flaps, with and without auxiliary vertical tail surfaces, and with different centers of gravity and trim coefficients. Results indicate serious reduction of stick-fixed longitudinal stability because of wing-tip stalling at high lift coefficient. Directional stability without vertical tail is undesirably low. Low effective dihedral should be maintained. Elevator and rudder control system is satisfactory.
Contributing Partner: UNT Libraries Government Documents Department