National Advisory Committee for Aeronautics (NACA) - 13 Matching Results

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Calibration and Measurement in Turbulence Research by the Hot-Wire Method

Description: "The problem of turbulence in aerodynamics is at present being attacked both theoretically and experimentally. In view of the fact however that purely theoretical considerations have not thus far led to satisfactory results the experimental treatment of the problem is of great importance. Among the different measuring procedures the hot wire methods are so far recognized as the most suitable for investigating the turbulence structure" (p. 1).
Date: June 1947
Creator: Kovasznay, Laszlo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compression Shocks of Detached Flow

Description: "It is known that compression shocks which lead from supersonic to subsonic velocity cause the flow to separate on impact on a rigid wall. Such shocks appear at bodies with circular symmetry or wing profiles on locally exceeding sonic velocity, and in Laval nozzles with too high a back pressure. The form of the compression shocks observed therein is investigated" (p. 1).
Date: June 1947
Creator: Eggink
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Description of Russian Aircraft Engines "AM 35" and "AM 38"

Description: The Russian AM 35 and AM 38 aircraft engines have superchargers with a swirl throttle, which appears to be a purely Russian development. This paper gives the results of test runs of the two engines, including the effects of the swirl throttle on engine performance.
Date: June 1947
Creator: Denkmeier, H. & Gross, K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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General Characteristics of the Flow through Nozzles at Near Critical Speeds

Description: The characteristics of the position and form of the transition surface through the critical velocity are computed for flow through flat and round nozzles from subsonic to supersonic velocity. Corresponding considerations were carried out for the flow about profiles in the vicinity of sonic velocity.
Date: June 1947
Creator: Sauer, R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lift Increase by Blowing Out Air, Tests on Airfoil of 12 Percent Thickness, Using Various Types of Flap

Description: "The NACA 23012-4 airfoil was investigated for the purpose of increasing lift by means of blowing out air from the wing, in conjunction with the effect of plain flap of variable contour and slotted flap of 25 percent chord length. The wing also was provided with a hinged nose, to be deflected at will. Air was blown out from the wing immediately in front of the flap; also at the opening between wing and hinged nose,tangentially to the surface of the wing" (p. 1).
Date: June 1947
Creator: Schwier, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure Recovery for Missiles with Reaction Propulsion at High Supersonic Speeds (The Efficiency of Shock Diffusers)

Description: "The problem of the intake of air is treated for a missile flying at supersonic speeds and of changing the kinetic energy of the air into pressure with the least possible losses. Calculations are carried out concerning the results which can be attained. After a discussion of several preliminary experiments, the practical solution of the problem at hand is indicated by model experiments. The results proved very satisfactory in view of the results which had been attained previously and the values… more
Date: June 1947
Creator: Oswatitsch, K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Six-Component Measurements on a Straight and a 35 Degree Swept-Back Trapezoidal Wing With and Without Split Flaps

Description: In accord with me test program (published in reference 7) the wing in question is briefly designated as No. 5. It differs from the rectangular wing discussed in reference 7 by its taper and from the 35 degree swept-back trapezoidal wing treated in reference 8 by the absence of sweepback.
Date: June 1947
Creator: Thiel, G. & Weissinger, F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Test Report on Three-and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio (Partial Report: Elliptic Wing)

Description: "The report UM No. 1023/1 which presented the results of measurements for a series of trapezoidal wings was the beginning of a series on wings with aspect ratio 1 to 3 and various contours. In report No. 1023/1 the aspect ratio (Lambda = 4/3) remained the same; the tapering was modified. The present report gives the results of the series of elliptic wings. Here the aspect ratio varies from 1 to 2 with the sweepback. The contour is formed by elliptic arcs. The influence of sweepback and contour … more
Date: June 1947
Creator: Lange & Wacke
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Investigation of Drag Reduction in Maintaining the Laminar Boundary Layer by Suction

Description: "Maintenance of a laminar boundary layer by suction was suggested recently to decrease the friction drag of an immersed body, in particular an airfoil section. The present treatise makes a theoretical contribution to this question in which, for several cases of suction and blowing, the stability of the laminar velocity profile is investigated. Estimates of the minimum suction quantities for maintaining the laminar boundary layer and estimates of drag reduction are thereby obtained" (p. 1).
Date: June 1947
Creator: Ulrich, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Three-Component Force and Mass-Flow Measurement on a Jet Nacelle

Description: The present report contains three-component forces and mass-flow measurements on a jet nacelle at small inlet-velocity ratios v(sub A)/v(sub o) < 1. The mass-flow measurement on two cross sections of the nacelle demonstrate the local-velocity distribution with varying flow and angle of attack.
Date: June 1947
Creator: Ilgmann, G. & Möller, E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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