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  • Cell & Developmental Biology  (1,205)
  • Life and Medical Sciences  (1,205)
  • Aerodynamics  (161)
  • 1945-1949  (593)
  • 1935-1939  (596)
  • 1925-1929
Collection
Keywords
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Years
Year
  • 1
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    Tests of Several Model Nacelle-Propeller Arrangements in Front of a Wing (1939)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: An investigation was conducted in the N.A.C.A. 20-foot wind tunnel to determine the drag, the propulsive and net efficiencies, and the cooling characteristics of severa1 scale-model arrangements of air-cooled radial-engine nacelles and present-day propellers in front of an 18- percent-thick, 5- by 15-foot airfoil. This report deals with an investigation of wing-nacelle arrangements simulating the geometric proportions of airplanes in the 40,000- to 70,000- pound weight classification and having the nacelles located in the vicinity of the optimum location determined from the earlier tests.
    Keywords: Aerodynamics
    Type: NACA-SR-123
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Wind-Tunnel Investigation of an N.A.C.A. 23012 Airfoil with a Slotted Flap and Three Types of Auxiliary Flap (1938)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: An investigation was made in the N.A.C.A. 7- by 10- foot wind tunnel to determine the aerodynamic section characteristics of an N. A. C. A. 23012 airfoil with a single main slotted flap equipped successively with auxiliary flaps of the plain, split, and slotted types. A test installation mas used in which an airfoil of 7-foot span was mounted vertically between the upper and the lower sides of the closed test section so that two-dimensional flow was approximated. On the basis of maximum lift coefficient, low drag at moderate and high lift coefficients, and high drag at high lift coefficients, the optimum combination of the arrangements was found to be the double slotted flap . All the auxiliary flaps tested, however, increased the magnitudes of the pitching moments over those of the main slotted flap alone.
    Keywords: Aerodynamics
    Type: NACA-SR-97
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Interference of Tail Surfaces and Wing and Fuselage from Tests of 17 Combinations in the N.A.C.A. Variable-Density Tunnel (1939)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: An investigation of the interference associated with tail surfaces added to wing-fuselage combinations was included in the interference program in progress in the NACA variable-density tunnel. The results indicate that, in aerodynamically clean combinations, the increment to the high-speed drag can be estimated from section characteristics within useful limits of accuracy. The interference appears mainly as effects on the downwash angel and as losses in the tail. An interference burble, which markedly increases the glide-path angle and the stability in pitch before the actual stall, may be considered a means of obtaining satisfactory stalling characteristics for a complete combination.
    Keywords: Aerodynamics
    Type: NACA-SR-98
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    High-Speed Tests of Radial-Engine Cowlings (1939)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: The drag characteristics of eight radial-engine cowlings have been determined over a wide speed range in the N.A.C.A. 8-foot high-speed wind tunnel. The pressure distribution over all cowlings was measured, to and above the speed of the compressibility burble, as an aid in interpreting the force tests. One-fifth-scale models of radial-engine cowlings on a wing-nacelle combination mere used in the tests.
    Keywords: Aerodynamics
    Type: NACA-SR-109
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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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
    Format: application/pdf
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  • 6
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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
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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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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  • 8
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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
    Format: application/pdf
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  • 9
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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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  • 10
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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
    Format: application/pdf
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