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  • Chemistry  (3,659)
  • Aerodynamics  (141)
  • 1945-1949  (3,800)
  • 1
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    Investigations of Compression Shocks and Boundary Layers in Gases Moving at High Speed (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The mutual influences of compression shocks and friction boundary layers were investigated by means of high speed wind tunnels.Schlieren optics provided a clear picture of the flow phenomena and were used for determining the location of the compression shocks, measurement of shock angles, and also for Mach angles. Pressure measurement and humidity measurements were also taken into consideration.Results along with a mathematical model are described.
    Keywords: Aerodynamics
    Type: NACA-TM-1113 , Mitteilungen aus dem Institut fuer Aerodynamik an der Eidgenoessischen Technischen Hochschule; 10
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  • 2
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    On the Vortex Sound from Rotating Rods (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The motion of different bodies imersed in liquid or gaseous media is accompanied by characteristic sound which is excited by the formation of unstable surfaces of separation behind the body, usually disintegrating into a system of discrete vortices(such as the Karman vortex street due to the flow about an infintely long rod, etc.).In the noise from fans,pumps,and similar machtnery, vortexnQif3eI?Yequently predominates. The purpose of this work is to elucidate certain questions of the dependence ofthis sound upon the aerodynamic parameters and the tip speed of the rotating rods,or blades. Although scme material is given below,insufficientto calculate the first rough approximation to the solution of this question,such as the mechanics of vortex formation,never the less certain conclusions maybe found of practical application for the reduction of noise from rotating blades.
    Keywords: Aerodynamics
    Type: NACA-TM-1136 , Zhurnal Tekhnicheskoi Fiziki; 14; 9; 561
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  • 3
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    High-Speed Aerodynamic Characteristics of a 1/7-Scale Model of the Northrop YB-49 Airplane (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Tests were conducted to find the effects of compressibility on the longitudinal stability and control of a 1/7-scale semispan model of the Northrop YB-49 airplane. Lift, drag, pitching moment, and elevon hinge moments were measured and are presented in graphical form. The results show that, due to a loss of lift on the outboard portion of the wing, the longitudinal static stability decreased rapidly as the Mach numbers increased above 0.735 the model experienced a climbing moment at positive lift coefficients. Also, a longitudinal-control effectiveness began to decrease at a Mach number of about 0.725
    Keywords: Aerodynamics
    Type: NACA-RM-A7C13
    Format: application/pdf
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  • 4
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    The Calculation of Compressible Flows with Local Regions of Supersonic Velocity (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: This report addresses a method for the approximate calculation of compressible flows about profiles with local regions of supersonic velocity. The flow around a slender profile is treated as an example.
    Keywords: Aerodynamics
    Type: NACA-TM-1114 , Forschungsbericht-1794 , Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters
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  • 5
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    The Lift Distribution of Swept-Back Wings (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Two procedures for calculating the lift distribution along the span are given in which a better account is taken of the distribution of circulation over te area than in the Prandtl lifting-line theory. The methods are also applicable to wing sweepback. Calculated results for the two methods were in agreement.
    Keywords: Aerodynamics
    Type: NACA-TM-1120 , Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters; 1553
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  • 6
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    Planing of Watercraft (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The present report deals with the processes accompanying the planing of a planing boat or a seaplane on water . The study is largely based upon theoretical investigations; mathematical problems and proofs are not discussed. To analyze theoreticaly actual planing processes, giving due consideration to all aspects of the problem, is probably not possible. The theories therefore treat various simple limiting cases, which in their entirety give a picture of the planing processes and enable the interpretation of the experimental results. The discussion is concerned with the stationary planing attitude: the boat planes at a constant speed V on an originally smooth surface.
    Keywords: Aerodynamics
    Type: NACA-TM-1139 , Jahrbuch der Schiffbautechnik; 34; 205-227
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  • 7
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    Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was determined in investigations of the complete engine in the NACA Cleveland altitude wind tunnel. Characteristics are presented as functions of the total-pressure ratio across the turbine and of turbine speed and gas flow corrected to sea-level conditions. Three turbine nozzles of different areas were used to determine the area that gave optimum performance. Inasmuch as tail-pipe nozzles of different diameters were investigated in combination with the standard turbine nozzle, the effect of varying discharge conditions on turbine operation could be observed. The investigations covered a range of pressure attitudes from 5000 to 40,000 feet. The engine was investigated over the entire operable range of speeds at each altitude. At pressure altitude of 30,000 feet, the effect on turbine operation of varying the ram pressure ration over a range from 1.10 to 1.77 was evaluated. An altitude effect was apparent when turbine pressure ratio was plotted against corrected turbine speed but it was so slight as to be negligible insofar as the turbine efficiencies were concerned. A maximum turbine efficiency of slightly more than 82 percent was obtained with the configuration using the standard turbine nozzle and the low-flow compressor. This efficiency, which is somewhat lower than the actual turbine efficiency, is uncorrected for accessories drive power, bearing friction, tail-pipe pressure drop, compressor thermal radiation, and introduction of turbine-disk cooling air into the gas stream. Changes in the ram pressure ratio had a negligible effect on the turbine efficiency.
    Keywords: Aerodynamics
    Type: NACA-RM-E8F09d
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  • 8
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    The Separation of Flow Due to Compressibility Shock (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: It is known that the compressibility shocks accompanying local or total supersonic flows lead to pronounced flow separations which result in unusually high energy losses on airplane wings, vanes, and in diffusers. These phenomena were investigated experimentally and theoretically.
    Keywords: Aerodynamics
    Type: NACA-TM-1152 , Technische Berichte Band; 10; 2; 59-61
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  • 9
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    Drag Reduction by Suction of the Boundary Layer Separated Behind Shock Wave Formation at High Mach Numbers (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: With an approach of the velocity of flight of a ship to the velocity of sound, there occurs a considerable increase of the drag. The reason for this must be found in the boundary layer separation caused by formation of shock waves. It will be endeavored to reduce the drag increase by suction of the boundary layer. Experimental results showed that drag increase may be considerably reduced by this method. It was, also, observed that, by suction, the position of shock waves can be altered to a considerable extent.
    Keywords: Aerodynamics
    Type: NACA-TM-1168 , ZWB-1424
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  • 10
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    Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation to determine the performance and operational characteristics of an axial-flow gas turbine-propeller engine was conducted in the Cleveland altitude wind tunnel. As part of this investigation, the combustion-chamber performance was determined at pressure altitudes from 5000 to 35,000 feet, compressor-inlet ram-pressure ratios of 1.00 and 1.09, and engine speeds from 8000 to 13,000 rpm. Combustion-chamber performance is presented as a function of corrected engine speed and corrected horsepower. For the range of corrected engine speeds investigated, overall total-pressure-loss ratio, cycle efficiency, and the fractional loss in cycle efficiency resulting from pressure losses in the combustion chambers were unaffected by a change in altitude or compressor-inlet ram-pressure ratio. For the range of corrected horsepowers investigated, the total-pressure-loss ratio and the fractional loss in cycle efficiency resulting from pressure losses in the combustion chambers decreased with an increase in corrected horsepower at a constant corrected engine speed. The combustion efficiency remained constant for the range of corrected horsepowers investigated at all corrected engine speeds.
    Keywords: Aerodynamics
    Type: NACA-RM-E8F10d
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