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 Serial/Series Title: NACA Advanced Confidential Report
 Collection: Technical Report Archive and Image Library
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
An additional investigation of the high-speed lateral-control characteristics of spoilers

An additional investigation of the high-speed lateral-control characteristics of spoilers

Date: June 1, 1945
Creator: Summers, James
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Correlation of the drag characteristics of a P-51B airplane obtained from high-speed wind-tunnel and flight tests

Correlation of the drag characteristics of a P-51B airplane obtained from high-speed wind-tunnel and flight tests

Date: February 1, 1945
Creator: Hamilton, William T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Extension of Useful Operating Range of Axial-Flow Compressors by Use of Adjustable Stator Blades

Extension of Useful Operating Range of Axial-Flow Compressors by Use of Adjustable Stator Blades

Date: January 1, 1948
Creator: Sinnette, John T & Voss, William J
Description: A theory has been developed for resetting the blade angles of an axial-flow compressor in order to improve the performance at speeds and flows other than the design and thus extend the useful operating range of the compressor. The theory is readily applicable to the resetting of both rotor and stator blades or to the resetting of only the stator blades and is based on adjustment of the blade angles to obtain lift coefficients at which the blades will operate efficiently. Calculations were made for resetting the stator blades of the NACA eight-stage axial-flow compressor for 75 percent of design speed and a series of load coefficients ranging from 0.28 to 0.70 with rotor blades left at the design setting. The NACA compressor was investigated with three different blade settings: (1) the design blade setting, (2) the stator blades reset for 75 percent of design speed and a load coefficient of 0.48, and (3) the stator blades reset for 75 percent of design speed and a load coefficient of 0.65.
Contributing Partner: UNT Libraries Government Documents Department
An interim report on the stability and control of tailless airplanes

An interim report on the stability and control of tailless airplanes

Date: October 1, 1944
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experiments on drag of revolving disks, cylinders and streamline rods at high speeds

Experiments on drag of revolving disks, cylinders and streamline rods at high speeds

Date: June 1, 1944
Creator: Regier, Arthur
Description: None
Contributing Partner: UNT Libraries Government Documents Department
On the flow of a compressible fluid by the hodography method II : fundamental set of particular flow solutions of the Chaplygin differential equation

On the flow of a compressible fluid by the hodography method II : fundamental set of particular flow solutions of the Chaplygin differential equation

Date: November 1, 1944
Creator: Kaplan, Carl
Description: None
Contributing Partner: UNT Libraries Government Documents Department