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  • Weitere Quellen  (63)
  • Aerodynamics  (34)
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  • 1950-1954  (46)
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  • 2010-2014
  • 1950-1954  (46)
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  • 1
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    Progress report, Seismological Laboratory, California Institute of Technology, 1952 (1953)
    In:  Trans. Am. Geophys. Union, Beijing, Pergamon, vol. 34, no. 3-4, pp. 785-791, pp. 1246
    Details
    Publikationsdatum: 1953
    Schlagwort(e): Seismology ; Project report/description ; EOS
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    BIBLIOGRAFIE SEISMOLOGIE
  • 2
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    Larger shocks of 1951 (1953)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 1951, no. 6, pp. 95, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1953
    Schlagwort(e): Earthquake catalog ; Seismology ; Seismicity
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    BIBLIOGRAFIE SEISMOLOGIE
  • 3
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    Wave velocities at depths between 50 and 600 kilometers (1953)
    In:  Bull. Seism. Soc. Am., Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 43, no. 6, pp. 223-232, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1953
    Schlagwort(e): Velocity analysis ; Seismology ; Earth model, also for more shallow analyses ! ; BSSA
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    BIBLIOGRAFIE SEISMOLOGIE
  • 4
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    Results from teleseismic records of the 1952 Kern County California, shocks (1953)
    In:  Bull. Geol. Soc. Am., Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 64, no. 6, pp. 1525, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1953
    Schlagwort(e): Seismology ; Seismometer ; Teleseismic events ; Earthquake
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    BIBLIOGRAFIE SEISMOLOGIE
  • 5
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    Larger shocks of 1952 (1953)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 1952, no. 6, pp. 104, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1953
    Schlagwort(e): Earthquake catalog ; Seismology ; Seismicity
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    BIBLIOGRAFIE SEISMOLOGIE
  • 6
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    Microseisms, microbaroms, storms and waves in western North America (1953)
    In:  Trans., Am. Geophys. Union, Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 34, no. 6, pp. 161-173, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1953
    Schlagwort(e): Micro seismicity ; Waves ; Seismology ; Meteorology ; NOISE ; EOS
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    BIBLIOGRAFIE SEISMOLOGIE
  • 7
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    Some general features of low-velocity layers (1953)
    In:  Bull. Geol. Soc. Am., Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 64, no. 6, pp. 1525, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1953
    Schlagwort(e): Low velocity layer ; Velocity analysis ; Seismology
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    BIBLIOGRAFIE SEISMOLOGIE
  • 8
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    Geophysical and geological observations in the Pacific area and tectonic hypotheses (1953)
    Pacific Science Association
    In:  7th Congress Proceedings New Zealand (1949), vol. 2, Wellington, Pacific Science Association, vol. 10, no. GL-TR-89-0230, pp. 7-9, (ISBN 3-933346-037)
    Details
    Publikationsdatum: 1953
    Schlagwort(e): Tectonics ; Seismology ; Geol. aspects
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    BIBLIOGRAFIE SEISMOLOGIE
  • 9
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    Travel times of longitudinal waves from surface foci (1953)
    Nat. Acad. Sci.
    In:  Proceedings, vol. 39, Washington, Nat. Acad. Sci., vol. 10, no. GL-TR-89-0230, pp. 849-853, (ISBN 3-933346-037)
    Details
    Publikationsdatum: 1953
    Schlagwort(e): Travel time ; Seismology ; P-waves
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    BIBLIOGRAFIE SEISMOLOGIE
  • 10
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    The background of flying or handling qualities (1953)
    In:  CASI
    Details
    Publikationsdatum: 2006-10-26
    Schlagwort(e): unknown
    Format: text
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  • 11
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    A simple laminar boundary layer with a secondary flow (1953)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-05-31
    Schlagwort(e): unknown
    Materialart: AD-12826
    Format: text
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  • 12
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    Theoretical performance of mixtures of liquid ammonia and hydrazine as fuel with liquid fluorine as oxidant for rocket engines (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-25
    Schlagwort(e): unknown
    Materialart: NACA-RM-E53F08 , AD-15617
    Format: application/pdf
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  • 13
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    Development of a supersonic area rule and an application to the design of a wing-body combination having high lift-to-drag ratios (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-25
    Schlagwort(e): unknown
    Materialart: NACA-RM-L53H31A
    Format: application/pdf
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  • 14
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    Theoretical performance of liquid ammonia and liquid fluorine as a rocket propellant (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-25
    Schlagwort(e): unknown
    Materialart: NACA-RM-E53A26 , AD-4226
    Format: application/pdf
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  • 15
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    Theoretical performance of liquid hydrogen and liquid fluorine as a rocket propellant (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-25
    Schlagwort(e): unknown
    Materialart: NACA-RM-E52L11 , AD-3625
    Format: application/pdf
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  • 16
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    Measurements in the boundary layer on a smooth flat plate in supersonic flow. 1- the problem of the turblent boundry layer (1953)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-05-25
    Schlagwort(e): unknown
    Materialart: JPL-20-69
    Format: text
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  • 17
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    Functions of prandtl-meyer angle for supersonic nozzle design (1953)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-05-25
    Schlagwort(e): unknown
    Materialart: JPL-PUBL.-26
    Format: text
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  • 18
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    Application of the time vector method to the analysis of flight test lateral oscillation data (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-25
    Schlagwort(e): unknown
    Materialart: CAL-FRM-189
    Format: text
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  • 19
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    Velocity of sound in liquid propellants (1953)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-05-22
    Schlagwort(e): unknown
    Materialart: JPL-TM-20-84
    Format: text
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  • 20
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    Storability of fuming nitric acid (1953)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-05-22
    Schlagwort(e): unknown
    Format: text
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  • 21
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    Performance Characteristics of Plane-Wall Two-Dimensional Diffusers (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Experiments have been made at Stanford University to determine the performance characteristics of plane-wall, two-dimensional diffusers which were so proportioned as to insure reasonable approximation of two-dimensional flow. All of the diffusers had identical entrance cross sections and discharged directly into a large plenum chamber; the test program included wide variations of divergence angle and length. During all tests a dynamic pressure of 60 pounds per square foOt was maintained at the diffuser entrance and the boundary layer there was thin and fully turbulent. The most interesting flow characteristics observed were the occasional appearance of steady, unseparated, asymmetric flow - which was correlated with the boundary-layer coalescence - and the rapid deterioration of flow steadiness - which occurred as soon as the divergence angle for maximum static pressure recovery was exceeded. Pressure efficiency was found to be controlled almost exclusively by divergence angle, whereas static pressure recovery was markedly influenced by area ratio (or length) as well as divergence angle. Volumetric efficiency. diminished as area ratio increased, and at a greater rate with small lengths than with large ones. Large values of the static-pressure-recovery coefficient were attained only with long diffusers of large area ratio; under these conditions pressure efficiency was high and. volumetric efficiency low. Auxiliary tests with asymmetric diffusers demonstrated that longitudinal pressure gradient, rather than wall divergence angle, controlled flow separation. Others showed that the addition of even a short exit duct of uniform section augmented pressure recovery. Finally, it was found that the installation of a thin, central, longitudinal partition suppressed flow separation in short diffusers and thereby improved pressure recovery
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-2888
    Format: application/pdf
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  • 22
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    Theoretical Performance Characteristics of Sharp Lip Inlets at Subsonic Speeds (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A method is presented for the estimation of the subsonic-flight-speed characteristics of sharp-lip inlets applicable to supersonic aircraft. The analysis, based on a simple momentum balance consideration, permits the computation of inlet pressure recovery - mass-flow relations and additive-drag coefficients for forward velocities from zero to the speed of sound. The penalties for operation of a sharp-lip inlet at velocity ratios other than 1.0 may be severe; at lower velocity ratios an additive drag is incurred that is not cancelled by lip suction, while at higher velocity ratios, unavoidable losses in inlet total pressure will result. In particular, at the take-off condition, the total pressure and the mass flow for a choked inlet are only 79 percent of the values ideally attainable with a rounded lip. Experimental data obtained at zero speed with a sharp-lip supersonic inlet model were in substantial agreement with the theoretical results.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-3004
    Format: application/pdf
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  • 23
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    On the Development of Turbulent Wakes from Vortex Streets (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Wake development behind circular cylinders at Reynolds numbers from 40 to 10,000 was investigated in a low-speed wind tunnel. Standard hotwire techniques were used to study the velocity fluctuations. The Reynolds number range of periodic vortex shedding is divided into two distinct subranges. At R = 40 to 150, called the stable range, regular vortex streets are formed and no turbulent motion is developed. The range R = 150 to 300 is a transition range to a regime called the irregular range, in which turbulent velocity fluctuations accompany the periodic formation of vortices. The turbulence is initiated by laminar-turbulent transition in the free layers which spring from the separation points on the cylinder. This transition first occurs in the range R = 150 to 300. Spectrum and statistical measurements were made to study the velocity fluctuations. In the stable range the vortices decay by viscous diffusion. In the irregular range the diffusion is turbulent and the wake becomes fully turbulent in 40 to 50 diameters downstream. It was found that in the stable range the vortex street has a periodic spanwise structure. The dependence of shedding frequency on velocity was successfully used to measure flow velocity. Measurements in the wake of a ring showed that an annular vortex street is developed.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-2913
    Format: application/pdf
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  • 24
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    Theoretical performance of liquid hydrazine and liquid fluorine as a rocket propellant (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-25
    Schlagwort(e): unknown
    Materialart: NACA-RM-E53E12 , AD-14599
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  • 25
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    Wind-Tunnel Investigation of a 1/60-Scale Model of the Republic MX-1554 Airplane at a Mach Number of 2.85 (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Schlagwort(e): unknown
    Materialart: NACA-RM-SA53C18
    Format: application/pdf
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  • 26
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    Wind-Tunnel Investigation of the Drag and Lateral-Stability Characteristics of a 1/22-Scale Model of a Bomber Airplane Employing a Low-Aspect-Ratio Triangular Wing (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Schlagwort(e): unknown
    Materialart: NACA-RM-SA53G08
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  • 27
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    Some factors contributing to scale effect at supersonic speeds (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Schlagwort(e): unknown
    Materialart: NASA-TM-X-60842 , AG8/M4 , AD-662965
    Format: text
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  • 28
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    The Base Pressure at Supersonic Speeds on Two-Dimensional Airfoils and Bodies of Revolution (With and Without Fins) Having Turbulent Boundary Layers (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: An analysis has been made of available experimental data to show the effects of most variables that are predominant in determining base pressure at supersonic speeds. Two dimensional bases and bases of bodies of revolution, restricted to turbulent boundary layers, are covered.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L53C02
    Format: application/pdf
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  • 29
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    Elastic Buckling under Combined Stresses of Flat Plates with Integral Waffle-Like Stiffening (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: Theory and experiment were compared and found in good agreement for the elastic Buckling under combined stresses of long flat plates with integral waffle-like stiffening in a variety of configurations. For such flat plates, 45deg waffle stiffening was found to be the most effective of the configurations for the proportions considered over the widest range of combinations of compression and shear.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L53J27
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  • 30
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    Rocket-Model Measurements of Zero-Lift Damping in Roll of the Bell MX-776 Missile at Mach Numbers from 0.6 to 1.56 (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: The zero-lift damping in roll of the Bell MX-776 missile has been measured by a sting-mounted rocket-model technique at Mach numbers from 0.6 to 1.56. The damping-in-roll data, in general, show no unusual variation with Mach number. Aileron rolling-moment effectiveness derived from these data and previously obtained rolling-effectiveness data appear reasonable,
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL54A13
    Format: application/pdf
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  • 31
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    Lateral Oscillatory Characteristics of the Republic F-91 Airplane Calculated by Using Low-Speed Experimental Static and Rotary Derivatives (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: The present investigation was conducted to determine, from low-speed tests in the Langley stability tunnel, the static and rotary derivatives of a 1/9-scale model of the Republic F-91 airplane and various of its components (including the effects of wing incidence) and to determine the accuracy with which the period and damping of the lateral oscillation of the airplane could be calculated by using these experimentally between flight and calculated period and damping of the lateral oscillation were made for Mach numbers from 0.4 to 0.9 at an altitude of 20,OOO feet for 0deg wing incidence and several other wing incidences. Some comparisons were made of the static and rotary derivatives of the model and derivatives estimated by available procedures. determined derivatives (corrected for Mach number effects). Comparisons The results of the investigation have indicated that the model did not have unusual aerodynamic characteristics except for a large (about -0.125) increment in the damping in yaw contributed by the fuselage. Changes in wing incidence, in general, had little effect on the static and rotary derivatives of the model. The static and rotary derivatives of the model could be estimated with good accuracy only in the low angle-of-attack range by using available procedures.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L53G01
    Format: application/pdf
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  • 32
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    An Exploratory Investigation of Some Types of Aeroelastic Instability of Open and Closed Bodies of Revolution Mounted on Slender Struts (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Aeroelastic instability phenomena of isolated open and closed rigid bodies of revolution free to move under elastic restraint have been investigated experimentally at low speeds by means of models suspended at zero angles of attack and yaw on slender flexible struts from a wind tunnel ceiling. Three types of instability were observed - flutter similar to classical bending-torsion flutter, divergence, and an uncoupled oscillatory instability which consists in nonviolent continuous or intermittent small-amplitude oscillations involving only angular deformations. The speeds at which this oscillatory instability starts were found to be as low as about one-third of the speed at flutter or divergence and to depend on the shape of the body, particularly that of the afterbody, and on the relative location of the elastic axis. An attempt has been made to calculate the airspeeds and, in the case of the oscillatory phenomena, the frequencies at which these instabilities occur by using slender-body theory for the aerodynamic forces on the bodies and neglecting the aerodynamic forces on the struts. However, the agreement between the speeds and frequencies calculated in this manner and those actually observed has been found to be generally unsatisfactory; with the exception of the frequencies of the uncoupled oscillations which could be predicted with fair accuracy. The nature of the observed phenomena and of the forces on bodies of revolution suggests that a significant improvement in the accuracy of analytical predictions of these aeroelastic instabilities can be had only by taking into account the effects of boundary-layer separation on the aerodynamic forces.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L53E07
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  • 33
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    Experimental investigation of combustion instability in rocket motors (1953)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-08-14
    Beschreibung: No abstract available
    Schlagwort(e): unknown
    Format: text
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  • 34
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    Flight Test Results of Rocket-Propelled Buffet-Research Models Having 45 Degree Sweptback Wings and 45 Degree Sweptback Tails Located in the Wing Chord Plane (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: Three rocket-propelled buffet-research models have been flight tested to determine the buffeting characteristics of a swept-wing- airplane configuration with the horizontal tail operating near the wing wake. The models consisted of parabolic bodies having 45deg sweptback wings of aspect ratio 3.56, at aspect ratio of 0.3, NACA 64A007 airfoil sections, and tail surfaces of geometry and section identical to the wings. Two tests were conducted with the horizontal tail located in the wing chord plane with fixed incidence angles of -1.5deg on one model and 0deg on the other model. The third test was conducted with no horizontal tail. Results of these tests are presented as incremental accelerations in the body due to buffeting, trim angles of attack, trim normal- and side-force coefficients, wing-tip helix angles, static-directional-stability derivatives , and drag coefficients plotted against Mach number. These data indicate that mild low-lift buffeting was experienced by all models over a range of Mach number from approximately 0.7 to 1.4. It is further indicated that this buffeting was probably induced by wing-body interference and was amplified at transonic speeds by the horizontal tail operating in the wing wake. A longitudinal trim change was encountered by the tail-on models at transonic speeds, but no large changes in side force and no wing dropping were indicated.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L53I10
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  • 35
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    Investigation of the Attenuation of Plane Shock Waves Moving over very Rough Surfaces (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: Experimental measurements of the attenuation of plane shock waves moving over rough walls have been made in a shock tube. Measurements of the boundary-layer characteristics, including thickness and velocity distribution behind the shock, have also been made with the aid of new cal techniques which provide direct information on the local boundary-layer conditions at the rough walls. Measurements of shock speed and shock pressure ratio are presented for both smooth-wall and rough-wall flow over lengths of machined-smooth and rough strips which lined all four walls of the shock tube. A simplified theory based on Von Karman's expression for skin-friction coefficient for flow over rough walls, along with a wave-model concept and extensions to include time effects, is presented. In this theory, the shock-tube flow is assumed to be one-dimensional at all times and the wave-model concept is used to relate the local layer growth to decreases in shock strength. This concept assumes that local boundary-layer growths act as local mass-flow sinks, which give rise to expansion waves which, in turn, overtake the shock and lower its mass flow accordingly.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL53D13A
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  • 36
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    Factors Affecting Laminar Boundary Layer Measurements in a Supersonic Stream (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-13
    Beschreibung: The observed discrepancy at supersonic speeds between theoretical and apparent experimental average flat plate friction-drag coefficients calculated from boundary layer total-pressure surveys was investigated. Effects of the total-pressure probe, heat transfer through the leading edge region, change in leading-edge radius and strength of the leading-edge wave, possible early transition to turbulent flow or bursts of turbulence, and the slight stream-wise pressure gradient inherent in flat plate flow were investigated for plates with very sharp leading edges. Only one of these factors, the effect of the total-pressure probe, was found to be significant. Total-pressure probes of different tip heights, when placed in laminar boundary layers developing under identical conditions, were found to yield different values of friction drag coefficient. Extrapolation of these measurements indicates that a probe of vanishing size would yield the theoretical predicted values of average flat plate friction-drag coefficients. A correlation describing the relation between the friction-drag discrepancy and the probe tip height is presented.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-2891
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  • 37
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    A Transonic Wind-Tunnel Investigation of the Trim and Dynamic Response Characteristics of the Horizontal Tail of a 1/7-Scale Model of the Complete Tail of the Grumman XF10F-1 Airplane (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: An investigation was made of the trim and dynamic response characteristics of the free-floating horizontal tail of a 1/7-scale model of the complete tail of the Grumman XF10F-1 airplane in the Langley 8-foot transonic tunnel at Mach numbers up to 1.13. The complete tail was mounted in the tunnel on a 3deg conical support body. Various configurations were investigated. A loss in damping of the horizontal tail at transonic speeds was shown by both tunnel and flight tests. The loss in damping extended over a greater Mach number range and the maximum loss occurred at a higher Mach number in the tunnel tests. Large-amplitude oscillations of the horizontal tail of the basic configuration which occurred at low supersonic Mach numbers appeared to be primarily due to the vertical tail of the basic configuration and the interference effects associated with this tail. Secondary factors contributing to the development of the large-amplitude oscillations of the horizontal tail of the basic configuration were probably the loss in damping of the horizontal tail at transonic speeds and the turbulence of the airstream itself.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL53D28
    Format: application/pdf
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  • 38
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    Theory of Wing-Body Drag at Supersonic Speeds (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: At subsonic speeds the pressure drag arising from the thickness of the body or wings is negligible so long as the shapes are sufficiently well streamlined to avoid flow separation. In that range there exists no possibility of either favorable or adverse interference on the pressure distributions themselves. If one body is so placed as to receive a drag from the pressure field of another then the second body is sure to receive a corresponding increment of thrust from the first. At supersonic speeds this tolerance, which was permitted the designer, disappears and the drag becomes sensitive to the shape and arrangement of the bodies.To be sure, the primary factor here is the thickness ratio, but nevertheless there exist arrangements in which a large cancellation of drag occurs.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-A53H18a
    Format: application/pdf
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  • 39
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    Calibration of the Friez Aerovane, Wind Measuring Set An/GMQ-11 (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: Calibrations of the Friez Aerovane, Wind Measuring Set AN/GMQ-11, manufactured by the Friez Instrument Division of the Bendix Aviation Corporation, were made in the Langley 300 MPH 7- by 10-foot tunnel at the request of the Signal Corps, U, S. Army. Two propellers snd two generators were tested through a speed range of 15 to 190 knots, The results indicated that at airspeeds greater than 80 knots the instrument indicated airspeeds higher than the tunnel airspeed..
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL53L23B
    Format: application/pdf
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  • 40
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    Recent Results Pertaining to the Application of the "Area Rule" (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: This paper is concerned primarily with the application of the "area rule" to the interpretation and improvement of the drag-rise characteristics of wing-body combinations at transonic and moderate supersonic speeds. Consideration of the general physical nature of the flow at transonic speeds, together with comparisons of the flow fields and drag-rise characteristics for wing-body combinations and bodies of revolution has led to the conclusion that near the speed of sound the drag rise for a thin low-aspect-ratio wing-body combination is primarily dependent on the axial distribution of cross-sectional area normal to the airstream (ref. 1). (The drag rise, sometimes referred to as pressure drag, is the difference between the drag level near the speed of sound and the drag level at subsonic speeds where the drag is due primarily to skin friction.) In order to illustrate the concept, figure 1 shows a wing-body combination and a body of revolution. A typical cross section normal to the airstream for the wing-body combination is shown at AA. The cross-sectional area of the wing is wrapped around the body of revolution so that the body has the same cross-sectional area at BB. All the other cross-sectional areas of the body of revolution are the same as those for the wing-body combination at the same axial stations. On the basis of the conclusion just stated, the drag rise for this body of revolution should be similar to that for the wing-body combination.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L53I15a
    Format: application/pdf
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  • 41
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    Investigation of a Half-Conical Scoop Inlet Mounted at Five Alternate Circumferential Locations around a Circular Fuselage Pressure-Recovery Results at a Mach Number 2.01 (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: The effects of inlet circumferential position around the fuselage on the characteristics of a half-conical scoop inlet having a 24.6deg half-angle cone have been investigated in the langley 4- by 4-foot supersonic pressure tunnel. Pressure-recovery results have been obtained at a Mach number of 2.01 for a fixed boundary-layer-bleed height which was 60 percent of the boundary-layer thickness at an angle of attack of 0deg, and for cowling position parameters of 42.4deg and 38.0deg. inlet had a capture area equal to 24.9 percent of the basic-fuselage frontal area. The angle of attack was varied from 0deg to 12deg. The most favorable pressure-recovery characteristics at angles of attack were obtained with the Inlet located on the bottom of the fuselage where the maximum recovery increased from a value of 81 percent at an angle of attack of 0deg to 87 percent at 12deg. In general, the pressure recovery decreased with increasing angle of attack for all other inlet locations. At a given angle of attack the pressure recovery decreased as the inlet location was progressively moved from the bottom to the top of the fuselage. Stable subcritical operation of the inlet with nearly constant pressure recovery was obtained for inlet mass-flow ratios from 1.0 to about 0.76 at an angle of attack of 0deg with the central body in the design position.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L53D30B
    Format: application/pdf
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  • 42
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    Drag Measurements on Equivalent Bodies of Revolution of Six Configurations of the Convair MX-1964 (Originally MX-1626) Proposed Supersonic Bomber (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-10
    Beschreibung: Tests on equivalent bodies of revolution of six configurations of the Consolidated Vultee Aircraft Corporation proposed supersonic bomber (Convair MX-1964) have indicated that it is possible to reduce the drag of the configuration by designing it to have a favorable area distribution. The method of NACA RM L53I22c to predict the peak pressure drag of a configuration on the basis of its area distribution gave generally good agreement with the subject models.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL53K04 , L-82024
    Format: application/pdf
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  • 43
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    High-Speed Wind-Tunnel Tests of a 1/16-Scale Model of the D-558 Research Airplane Lift and Drag Characteristics of the D-558-1 and Various Wing and Tail Configurations (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: Tests were made in the Langley 8-foot high-speed tunnel to investigate the aerodynamic characteristics of the D-558-1 airplane and various wing and tail configurations on the D-558-1 fuselage. The various wing and tail configurations were tested to determine the aerodynamic effects of aspect ratio and sweep for suitable use on the second phase of the D-558 project (D-558-2). The tests were conducted through a speed range from a Mach number of 0.40 to approximately 0.94.This part of the investigation includes the lift and drag results available for the configurations tested at this rate. The D-558-1 results indicated that the lift force break would occur at a Mach number of 0.85 with some reduction in lift at speeds above this Mach number. Tests indicated that the airplane will have satisfactory lift and drag characteristics up to and including its design Mach number of 0.85. The 35deg sweptback, 35deg swept-forward, and low-aspect-ratio (2.0) wing configurations all showed pronounced improvements in maintaining lift throughout the Mach number range tested and in increasing the critical speeds above the D-558-1 value &itical to critical Mach numbers on the order of 0.9. Insofar as lift and drag characteristics are concerned level flight at speeds approaching the velocity of sound appears practical if swept or low-aspect-ratio configurations similar to those tested are used.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L6J09
    Format: application/pdf
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  • 44
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    Low-Speed Longitudinal Stability Characteristics of a 1/6-Scale Model of the Republic XF-84H Airplane with the Propeller Operating (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: A low-speed investigation was made of a 1/6-scale model of the Republic XF-84H airplane. The model had a single tractor propeller and a 40deg swept wing of aspect ratio 3.45. This investigation was undertaken to provide information on the effects of propeller operation on longitudinal stability characteristics for the XF -84H airplane and to provide an indication of slipstream effects that might be encountered on similar swept-wing configurations. Effects of propeller operation were generally destabilizing for all conditions investigated; however, the over-all stability characteristics with power on were greatly dependent on the power-off characteristics. With flaps and slats retracted, longitudinal instability was present at moderate angles of attack both with the propeller off and with power on. The longitudinal stability with flaps and slats deflected, which was satisfactory without power, was decreased by propeller operation, but no marked pitch-up tendency was indicated. Significant improvement in the power-on stability with flaps retracted was achieved by use of either a wing fence at 75 percent semispan, a leading-edge chord-extension from 65 to 94 percent semispan, or a raised horizontal tail located 65 percent semispan above the thrust line.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL-53F26
    Format: application/pdf
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  • 45
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    Drag and Longitudinal Trim at Low Lift of the North American YF-100A Airplane at Mach Numbers from 0.76 to 1.77 as Determined from the Flight Test of a 0.11-Scale Rocket Model (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Drag and longitudinal trim at low lift of the North American YF-100A airplane at Mach numbers from 0.76 to 1.77 as determined from the flight test of a 0.11-scale rocket model are presented herein. Also included are some longitudinal stability and some qualitative pitch-damping data. The subsonic external-drag-coefficient level was about 0.012, and the supersonic level was about 0.043. The drag rise occurred at a Mach number of 0.95. The longitudinal trim change at low lift consisted basically of a mild nose-up tendency at a Mach number of 0.90. An indication of wing flutter was present at Mach numbers from 0.95 to 1.11. However, the full-scale airplane wing has approximately twice the scaled first-bending frequency as the model tested and, hence, will probably be free of this type of flutter. The aerodynamic-center location was 71 percent behind the leading edge of the mean aerodynamic chord at a Mach number of 1.03 and 62 percent at a Mach number of 1.74. Qualitative measurement of damping in pitch indicates that at low lift coefficients damping will be low at a Mach number of 1.03.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL53E11a
    Format: application/pdf
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  • 46
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    Summary of Rocket-Model Tests at Zero Lift of the Northrop MX-775B Missile Configuration from Mach Numbers of 0.9 to 1.8 (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Flight tests were conducted between Mach numbers of 0.9 and 1.8 over a Reynolds number range of 9(exp 6) to 30(exp 6) to determine the zero-lift drag and some rolling-effectiveness characteristics of the Northrop MX -775B missile with small and large body. The MX-775B is a proposed long range, supersonic, ground-to-ground missile having an arrow wing with 67.5 degree leading-edge sweep, 15 deg trailing-edge sweep, and a modified NACA 0004 airfoil section. The configuration has no horizontal tail but has wing trailing-edge elevons which serve a dual purpose as elevators and ailerons. The ratio of body frontal area to wing plan-form area is 0.0127 for the small-body configuration and 0.0330 for the large-body configuration. Five 1/4-scale models were flown permitting determination of the drag coefficient for the basic small-body configuration, the incremental drag due to the large body, the incremental drag resulting from a blunt wing trailing edge, the wing-plus-interference drag, and some rolling-effectiveness data. Results indicated that the MX-775B has low supersonic zero-lift drag, the maximum zero-lift drag coefficients being respectively 0.0125 and 0.0155 at a Mach number of M = 1803 for the small- and large-body configurations. The effect of a blunt wing trailing edge, obtained by cutting off 10 percent of the wing chord, was to increase the zero-lift drag by 13 to 21 percent. Wing-plus-interference drag accounted for 78 percent of the total drag at M = 0.9 and 70 percent at M = 195 for the small-body configuration. The ailerons produced positive rolling effectiveness for the wing stiffness of the test models and the dynamic pressures of the test.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL53J02
    Format: application/pdf
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  • 47
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    Earthquakes and structure in Southern California (1943)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 54, no. 6, pp. 499-526, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1943
    Schlagwort(e): Seismology ; Earth model, also for more shallow analyses !
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    BIBLIOGRAFIE SEISMOLOGIE
  • 48
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    Seismological evidence for roots of mountains (1943)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 54, no. 6, pp. 473-498, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1943
    Schlagwort(e): Seismology ; Earth model, also for more shallow analyses !
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    BIBLIOGRAFIE SEISMOLOGIE
  • 49
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    Recent results of earthquake study in Southern California (1943)
    In:  Trans., Am. Geophys. Union, Milano, Gustav Fischer, vol. 24, no. 6, pp. 95-96, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1943
    Schlagwort(e): Seismology ; Seismicity ; EOS
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    BIBLIOGRAFIE SEISMOLOGIE
  • 50
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    Effect of Normal Pressure on the Critical Shear Stress of Curved Sheet (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: In order to determine the critical stresses caused by an outward acting pressure on the upper surface of a wing due to the difference in internal and external pressures, torsional tests were made on two curved-sheet specimens subjected to an outward acting normal pressure. Results show that an outward acting normal pressure appreciable raises the critical shear stress for an unstiffened curved sheet; the absolute increase in critical shear stress is slightly greater for a 30 in. rib spacing than for a 10 in. rib spacing.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-416
    Format: application/pdf
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  • 51
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    Wind-Tunnel Investigation of a Revised Horizontal Tail Surface for the Grumman TBF-1 Airplane (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: No abstract available
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-702
    Format: application/pdf
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  • 52
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    Drag Measurements of a Protruding .50-caliber Machine Gun with Barrel Jacket Removed (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Tests were made in 8-ft high-speed wind tunnel to determine the drag reduction possible by eliminating the barrel jacket of a protruding 50-caliber aircraft gun. It was found that the drag of a standard aircraft gun protruding into the air stream at right angles to the flow can be reduced by 23% by discarding the barrel jacket. At 300 mph and sea-level conditions, this amounts to a decrease in drag of from 83 to 64 pounds. A rough surface finish on the barrel was found to have no adverse effects on the drag of the barrel, the drag being actually less at high Mach Numbers.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-581
    Format: application/pdf
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  • 53
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    Flight Tests of Various Tail Modifications on the Brewster XSBA-1 Airplane II : Measurements of Flying Qualities with Tail Configuration Number Two (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Several tail modifications of the Brewster XSBA-1 scout-bomber were investigated and results compared. Modifications consisted of variation of the chord of the elevator and rudder while the total area of the surfaces is kept constant and variations of the total area of the vertical tail surface. Configuration number 2 reduced trim changes by 50 percent and reduced average elevator control force gradient from 30 to 27 pounds/g. Stick travel required to stall in maneuver was 4.6 inches.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-598
    Format: application/pdf
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  • 54
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    Wind Tunnel Tests of Ailerons at Various Speeds I : Ailerons of 0.20 Airfoil Chord and True Contour with 0.35 Aileron-chord Extreme Blunt Nose Balance on the NACA 66,2-216 Airfoil (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Hinge-moment, lift, and pressure-distribution measurements were made in the two-dimensional test section of the NACA stability tunnel on a blunt-nose balance-type aileron on an NACA 66,2-216 airfoil at speeds up to 360 miles per hour corresponding to a Mach number of 0.475. The tests were made primarily to determine the effect of speed on the action of this type of aileron. The balance-nose radii of the aileron were varied from 0 to 0.02 of the airfoil chord and the gap width was varied from 0.0005 to 0.0107 of the airfoil chord. Tests were also made with the gap sealed.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-431 , NACA-ACR-3F11
    Format: application/pdf
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  • 55
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    Wind-Tunnel Investigation of a Plain Aileron with Various Trailing-Edge Modifications on a Tapered Wing III : Ailerons with Simple and Spring-Linked Balancing Tabs (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Aerodynamics data are obtained for the design of linked balancing tabs and effect of varied tab span and location to produce suitable lateral control characteristics with reasonable stick pressures for high-speed aircraft. Simple and spring-linked balancing tabs may considerably reduce control pressures if aileron system is designed for low maximum aileron deflection. Spring-linked tabs also decrease variation of stick pressure with speed and impart better controlllability at low speeds.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-470
    Format: application/pdf
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  • 56
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    Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to those obtained with other high-lift devices on conventional airfoils for similar lift coefficients.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-697 , NACA-ACR-3I20
    Format: application/pdf
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  • 57
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    Wind-Tunnel Investigation of the Characteristics of Blunt-Nose Ailerons on a Tapered Wing (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Characteristics are determined for various modifications of 0.155-chord blunt-nose aileron on semispan model of tapered fighter plane wing. Ailerons with 40 percent nose balance reduced high-speed stick forces. Increased balance chord increases effectiveness and reduces high-speed stick forces. Increased balance chord increases effectiveness and reduces adverse effects of gap at aileron hose. Increase of nose radii increased negative slope of curve hinge-movement coefficient plotted against deflection. Extended deflection range decreased aileron effectiveness for small deflections but increased it at large deflections. Peak pressures at noses of ailerons are relatively high at moderate deflections.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-262
    Format: application/pdf
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  • 58
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    The Effect of Mass Distribution on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Free-Flight Tunnel (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The effects of mass distribution on lateral stability and control characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rolling and yawing movements of inertia were increased from normal values to values up to five times normal. For each moment-of-inertia condition, combinations of dihedral and vertical-tail area representing a variety of airplane configurations were tested. The results of the flight tests of the model were correlated with calculated stability and control characteristics and, in general, good agreement was obtained. The tests showed the following effects of increased rolling and yawing moments of inertia: no appreciable change in spiral stability; reductions in oscillatory stability that were serious at high values of dihedral; a reduction in the sensitivity of the model to gust disturbances; and a reduction in rolling acceleration provided by the ailerons, which caused a marked increase in time to reach a given angle of bank. The general flight behavior of the model became worse with increasing moments of inertia but, with combinations of small effective dihedral and large vertical-tail area, satisfactory flight characteristics were obtained at all moment-of-inertia conditions.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-388 , NACA-ARR-3H31
    Format: application/pdf
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  • 59
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    Methods of Measurement of High Air Velocities by the Hot-wire Method (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Investigations of strengths of hot wires at high velocities were conducted with platinum, nickel, and tungsten at approximately 200 Degrees Celcius hot-wire temperature. The results appear to disqualify platinum for velocities approaching the sonic range; whereas nickel withstands sound velocity, and tungsten may be used for supersonic velocities under standard atmospheric conditions. Hot wires must be supported by rigid prolongs at high velocities to avoid wire breakage. Resting current measurements for constant temperature show agreement with King's relation.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-880
    Format: application/pdf
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  • 60
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    A preliminary theoretical calculation of a propulsion system for the hydrobomb unit (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-14
    Beschreibung: No abstract available
    Schlagwort(e): unknown
    Materialart: PR-2
    Format: text
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  • 61
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    Preliminary Investigation of the Effect of Compressibility on the Maximum Lift Coefficient, Special Report (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Preliminary data are presented on the variation of the maximum lift coefficient with Mach number. The data were obtained from tests in the 8-foot high-speed tunnel of three NACA 16-series airfoils of 1-foot chord. Measurements consisted primarily of pressure-distribution measurements in order to illustrate the nature of the phenomena. It was found that the maximum lift coefficient of airfoils is markedly affected by compressibility even at Mach numbers as low as 0.2. At high Mach numbers pronounced decrease of the maximum lift coefficient was found. The magnitude of the effects of compressibility on the maximum lift coefficient and the low speeds at which these effects first appear indicate clearly that consideration of the take-off thrust for propellers will give results seriously in error if these considerations are based on the usual low-speed maximum-lift-coefficient data generally used.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-ACR-246 , NACA-SR-246
    Format: application/pdf
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  • 62
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    The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: The development of the laminar boundary layer in a compressible fluid is considered. Formulas are given for determining the boundary-layer thickness and the ratio of the boundary-layer Reynolds number to the body Reynolds number for airfoils and bodies of revolution. It i s shown that the effect of compressibility will profoundly alter the Reynolds number corresponding to the upper limit of the range of the low-drag coefficients . The available data indicate that for low-drag and high critical compressibility speed airfoils and bodies of revolution, this effect is favorable.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-ACR-252 , NACA-SR-252
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    Limitations of Lifting-Line Theory for Estimation of Aileron Hinge-Moment Characteristics (1943)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Hinge-moment parameters for several typical ailerons were calculated from section data with the aspect-ratio correction as usually determined from lifting-line theory. The calculations showed that the agreement between experimental and calculated results was unsatisfactory. An additional aspect-ratio correction, calculated by the method of lifting-surface theory, was applied to the slope of the curve of hinge-moment coefficient against angle of attack at small angles of attack. This so-called streamline-curvature correction brought the calculated and experimental results into satisfactory agreement.
    Schlagwort(e): Aerodynamics
    Materialart: AD-A801563 , NACA-WR-L-281 , NACA-CB-3L02
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
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