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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Technical Reports
 Collection: National Advisory Committee for Aeronautics Collection
Blockage Corrections for Three-Dimensional-Flow Closed-Throat Wind Tunnels, with Consideration of the Effect of Compressibility

Blockage Corrections for Three-Dimensional-Flow Closed-Throat Wind Tunnels, with Consideration of the Effect of Compressibility

Date: January 1, 1951
Creator: Herriot, J. G.
Description: Theoretical blockage corrections are presented for a body of revolution and for a three-dimensional, unswept wing in a circular or rectangular wind tunnel. The theory takes account of the effects of the wake and of the compressibility of the fluid, and is based on the assumption that the dimensions of the model are small in comparison with those of the tunnel throat. Formulas are given for correcting a number of the quantities, such as dynamic pressure and Mach number, measured in wind tunnel tests. The report presents a summary and unification of the existing literature on the subject.
Contributing Partner: UNT Libraries Government Documents Department
General Potential Theory of Arbitrary Wing Sections

General Potential Theory of Arbitrary Wing Sections

Date: December 1, 1979
Creator: Theodorsen, T.
Description: The problem of determining the two dimensional potential flow around wing sections of any shape is examined. The problem is condensed into the compact form of an integral equation capable of yielding numerical solutions by a direct process. An attempt is made to analyze and coordinate the results of earlier studies relating to properties of wing sections. The existing approximate theory of thin wing sections and the Joukowski theory with its numerous generalizations are reduced to special cases of the general theory of arbitrary sections, permitting a clearer perspective of the entire field. The method which permits the determination of the velocity at any point of an arbitrary section and the associated lift and moments is described. The method is also discussed in terms for developing new shapes of preassigned aerodynamical properties.
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
The 7 by 10 foot wind tunnel of the National Advisory Committee for Aeronautics

The 7 by 10 foot wind tunnel of the National Advisory Committee for Aeronautics

Date: January 1, 1933
Creator: Harris, Thomas A
Description: This report presents a description of the 7 by 10 foot wind tunnel and associated apparatus of the National Advisory Committee for Aeronautics. Included also are calibration test results and characteristic test data of both static force tests and autorotation tests made in the tunnel.
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
Design of Wind Tunnels and Wind Tunnel Propellers, II

Design of Wind Tunnels and Wind Tunnel Propellers, II

Date: January 1, 1921
Creator: Norton, F. H.
Description: No abstract available.
Contributing Partner: UNT Libraries Government Documents Department
Determination of Stresses in Gas-turbine Disks Subjected to Plastic Flow and Creep

Determination of Stresses in Gas-turbine Disks Subjected to Plastic Flow and Creep

Date: January 1, 1948
Creator: Manson, S. S.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Fuselage stress analysis

Fuselage stress analysis

Date: January 1, 1920
Creator: Warner, Edward P
Description: Report analyzes the stresses in a fuselage of the built-up type in which the shear is taken by diagonal bracing wires. Tests are conducted for landing, flying, and thrust loads.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel balances

Wind tunnel balances

Date: January 1, 1920
Creator: Warner, Edward P
Description: Report embodies a description of the balance designed and constructed for the use of the National Advisory Committee for Aeronautics at Langley Field, and also deals with the theory of sensitivity of balances and with the errors to which wind tunnel balances of various types are subject.
Contributing Partner: UNT Libraries Government Documents Department
Slip-stream corrections performance computation

Slip-stream corrections performance computation

Date: January 1, 1920
Creator: Warner, Edward P
Description: This report is an analysis of experiments performed by Eiffel on the air velocity in slip stream of a propeller, and also includes a theoretical discussion of the magnitude of the velocity in different propellers.
Contributing Partner: UNT Libraries Government Documents Department