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  • Inorganic Chemistry  (17.906)
  • Life and Medical Sciences  (10.562)
  • AERODYNAMICS  (4.602)
  • 1995-1999  (5.792)
  • 1980-1984  (9.013)
  • 1975-1979  (7.732)
  • 1960-1964  (4.647)
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  • 1910-1914  (3.638)
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  • 1
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    Curved-flow, rolling-flow, and oscillatory pure-yawing wind-tunnel test methods for determination of dynamic stability derivatives (1981)
    In:  CASI
    Details
    Publikationsdatum: 2011-10-14
    Beschreibung: The test capabilities of the Stability Wind Tunnel of the Virginia Polytechnic Institute and State University are described, and calibrations for curved and rolling flow techniques are given. Oscillatory snaking tests to determine pure yawing derivatives are considered. Representative aerodynamic data obtained for a current fighter configuration using the curved and rolling flow techniques are presented. The application of dynamic derivatives obtained in such tests to the analysis of airplane motions in general, and to high angle of attack flight conditions in particular, is discussed.
    Schlagwort(e): AERODYNAMICS
    Materialart: AGARD Dyn. Stability Parameters; 13 p
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  • 2
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    Buffeting tests in a cryogenic windtunnel (1995)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-24
    Beschreibung: Measurements of wing buffeting, using root strain gages, were made in the NASA Langley 0.3 m cryogenic wind tunnel to refine techniques which will be used in larger cryogenic facilities such as the United States National Transonic Facility (NTF) and the European Transonic Wind Tunnel (ETW). The questions addressed included the relative importance variations in frequency parameter and Reynolds number, the choice of model material (considering both stiffness and damping) and the effects of static aeroelastic distortion. The main series of tests was made on three half models of slender 65 deg delta wings with a sharp leading edge. The three delta wings had the same planform but widely differing bending stiffnesses and frequencies (obtained by varying both the material and the thickness of the wings). It was known that the steady flow on this configuration would be insensitive to variations in Reynolds number. On this wing at vortex breakdown the spectrum of the unsteady excitation is unusual, having a sharp peak at particular frequency parameter. Additional tests were made on one unswept half-wing of aspect ratio 1.5 with an NPL 9510 aerofoil section, known to be sensitive to variations in Reynolds number at transonic speeds. The test Mach numbers were M = 0.21 and 0.35 for the delta wings and to M = 0.30 for the unswept wing. On this wing the unsteady excitation spectrum is fairly flat (as on most wings). Hence correct representation of the frequency parameter is not particularly important.
    Schlagwort(e): AERODYNAMICS
    Materialart: Aeronautical Journal (ISSN 0001-9240); 99; 981; p. 1-14
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  • 3
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    Economy of flight at supersonic speeds (1976)
    In:  CASI
    Details
    Publikationsdatum: 2010-11-08
    Beschreibung: Prandtl's theory is used to determine the airflow over bodies and wings adapted to supersonic flight. By making use of these results, and by incorporating in them an allowance for the probable skin friction, some estimates of expected lift-drag ratios are made for various flight speeds with the best configuration. At each speed a slender body and wings having the best angle of sweepback are considered. For the range of supersonic speeds shown an airplane of normal density and loading would be required to operate at an altitude of the order of 60,000 feet. The limiting value of 1-1/2 times the speed of sound corresponds to a flight speed of 1000 miles per hour. At this speed about 1.5 miles per gallon of fuel are expected. It is interesting to note that this value corresponds to a value of more than 15 miles per gallon when the weight is reduced to correspond to that of an ordinary automobile.
    Schlagwort(e): AERODYNAMICS
    Materialart: Collected Works of Robert T. Jones; p 499-514
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  • 4
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    Aeroelastic characteristics of an oblique wing (1976)
    In:  CASI
    Details
    Publikationsdatum: 2010-11-08
    Beschreibung: In theory, the most efficient wing shape for transonic and low supersonic speeds is simply a long narrow straight subsonic wing turned at an oblique angle to the flight direction. This theory has been verified by tests at Mach numbers from .6 to 1.4 in supersonic wind tunnel and by comparative studies of transonic transport designs.
    Schlagwort(e): AERODYNAMICS
    Materialart: Collected Works of Robert T. Jones; p 867-883
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  • 5
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    Aerodynamic design for supersonic speeds (1976)
    In:  CASI
    Details
    Publikationsdatum: 2010-11-08
    Beschreibung: Recent theoretical and experimental work in supersonic aerodynamics is reviewed with its practical application in mind. Several arrangements of supporting surfaces and bodies are discussed and in some cases comparisons of theory and experiment are made. Finally, certain phenomena connected with lift and drag in a rarefied medium are considered briefly.
    Schlagwort(e): AERODYNAMICS
    Materialart: Collected Works of Robert T. Jones; p 625-644
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  • 6
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    Theoretical determination of the minimum drag of airfoils at supersonic speeds (1976)
    In:  CASI
    Details
    Publikationsdatum: 2010-11-08
    Beschreibung: A method is reported for determining mathematically the combined disturbance field, and in certain cases the minimum drag, of wings at supersonic speeds. The simplest analytic example is provided by the wing of elliptic planform, which achieves its minimum drag when the lift is distributed uniformly over the surface. With a symmetrical distribution of thickness, the requirement of minimum drag for a given total volume is found to lead to profiles of constant curvature.
    Schlagwort(e): AERODYNAMICS
    Materialart: Collected Works of Robert T. Jones; p 567-578
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  • 7
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    The minimum drag of thin wings in frictionless flow (1976)
    In:  CASI
    Details
    Publikationsdatum: 2010-11-08
    Beschreibung: The assumptions of the thin airfoil theory are found to provide certain necessary conditions for the minimum drag of airfoils having a given total lift, a given maximum thickness, or a given volume. The conditions are applicable to steady or unsteady motions and to subsonic or supersonic speeds without restriction on the planform. The computation of drag and the statement of the conditions for minimum drag depend on the consideration of a combined flow field, which is obtained by superimposing the disturbance velocities in forward and reversed motions. If the planform of the airfoil and its total lift are given, it is found that, for minimum drag, the lift must be distributed in such a way that the downwash in the combined field is constant over the entire planform. If the planform is given and the thickness of the airfoil is required to contain a specified volume, then the thickness must be distributed over the planform in such a way that the pressure gradient of the combined field in the direction of flight is constant at all points of the wing.
    Schlagwort(e): AERODYNAMICS
    Materialart: Collected Works of Robert T. Jones; p 557-565
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  • 8
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    Calculation of the motion of an airplane under the influence of irregular disturbances (1976)
    In:  CASI
    Details
    Publikationsdatum: 2010-11-08
    Beschreibung: The application of mathematical advances made in electricity and other branches to problems of airplane dynamics is demonstrated. The Heaviside-Bromwich methods of solution of linear differential equations are described and it is shown how these methods avoid the consideration of boundary conditions and of particular or complementary integrals. It is pointed out that if the solution of the differential equation is obtained for the case of a unit disturbance, the effect of varying disturbances may be found therefrom by Carson's theorem. A graphical solution of Carson's integral for irregular disturbances is given. The procedure of obtaining unit solutions of the equations is then taken up and the analogy between Heaviside's symbolic series solution and a physical procedure of approximation is shown. It is suggested that a fictitious impulsive disturbance be used in the treatment of initial motions.
    Schlagwort(e): AERODYNAMICS
    Materialart: Collected Works of Robert T. Jones; p 21-29
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  • 9
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    Three-dimensional wings of minimum pressure drag (1976)
    In:  CASI
    Details
    Publikationsdatum: 2010-11-08
    Beschreibung: In linearized flow theory, certain very interesting extremal properties of wings can be derived under rather broad conditions without the use of a complicated mathematical apparatus. The present chapter reviews certain results of this theory and indicates some rather obvious extensions to incorporate various auxiliary conditions. Several examples illustrating the relation between the geometrical features of the wing and the lift distribution for minimum drag are given.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Ames Res. Center Collected Works of Robert T. Jones; p 645-656
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  • 10
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    Some recent developments in the aerodynamics of wings for high speeds (1976)
    In:  CASI
    Details
    Publikationsdatum: 2010-11-08
    Beschreibung: The items discussed are: (1) a recently proposed correction formula for the effect of compressibility in two dimensional subsonic flow; (2) the equivalence rule and the area rule for transonic speeds; (3) reciprocal relations in linearized wing theory; and (4) some general results connected with the problem of minimum wave resistance. The paper concludes with an example showing indentation of the fuselage to obtain favorable interference with the wing at supersonic speeds.
    Schlagwort(e): AERODYNAMICS
    Materialart: Collected Works of Robert T. Jones; p 601-608
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  • 11
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    Theoretical correction for the lift of elliptic wings (1976)
    In:  CASI
    Details
    Publikationsdatum: 2010-11-08
    Beschreibung: In the wing section theory the magnitude of the circulation, and hence of the lift, is determined by the velocity that would be induced near the trailing edge of the section in a non-lifting potential flow. In three dimensional flow the problem is complicated by the presence of the wake and no simple basic solution has been found. Treatment of the problem of a wing of finite span is reported on the basis of the two dimensional theory, corrected for the effect of the wake.
    Schlagwort(e): AERODYNAMICS
    Materialart: Collected Works of Robert T. Jones; p 245-249
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  • 12
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    Reduction of wave drag by antisymmetric arrangement of wings and bodies (1976)
    In:  CASI
    Details
    Publikationsdatum: 2010-11-08
    Beschreibung: In theory, antisymmetric arrangements of wings and bodies can have smaller wave drag than corresponding mirror-symmetric arrangements. Thus, a long narrow oblique wing which presents the same aspect for two opposite directions of flight is potentially more efficient than corresponding (i.e., structurally equivalent) swept wing. The single continuous wing panel also adapts itself more readily to varying angles of obliquity, and hence, to varying flight speeds. Previous work on the aerodynamics and flight stability of oblique wing combinations is reviewed and a possible mode of application to transport aircraft operating at moderate supersonic speeds is suggested.
    Schlagwort(e): AERODYNAMICS
    Materialart: Collected Works of Robert T. Jones; p 657-664
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  • 13
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    The compressibility rule for drag of airfoil noses (1976)
    In:  CASI
    Details
    Publikationsdatum: 2010-11-08
    Beschreibung: It is shown that the drag of any semi-infinite airfoil section in purely subsonic inviscid flow follows precisely the Prandtl-Glauert compressibility rule. The result for the parabola has application to leading edge corrections in thin airfoil theory.
    Schlagwort(e): AERODYNAMICS
    Materialart: Collected Works of Robert T. Jones; p 619-623
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  • 14
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    Possibilities of efficient high-speed transport airplanes (1976)
    In:  CASI
    Details
    Publikationsdatum: 2010-11-08
    Beschreibung: Comparisons of wing-body combinations may not disclose the full effect of a loss in aerodynamic efficiency. If the thrust needs to be increased at a given altitude then more or larger engines will have to be used and the possibility of concealing them becomes less. In this process the lift drag ratio of the complete airplane may become still more unfavorable than indicated by the comparison. Primarily aerodynamic and structural considerations point toward the development of turbojet engines specifically adapted to operation in an atmosphere of one tenth normal density. In addition to the numerous other technological problems associated with operation at these high altitudes, the problems of safe descent and effective limitation to low speeds at low altitudes seem important.
    Schlagwort(e): AERODYNAMICS
    Materialart: Collected Works of Robert T. Jones; p 579-592
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  • 15
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    Leading-edge singularities in thin-airfoil theory (1976)
    In:  CASI
    Details
    Publikationsdatum: 2010-11-08
    Beschreibung: If the thin airfoil theory is applied to an airfoil having a rounded leading edge, a certain error will arise in the determination of the pressure distribution around the nose. It is shown that the evaluation of the drag of such a blunt nosed airfoil by the thin airfoil theory requires the addition of a leading edge force, analogous to the leading edge thrust of the lifting airfoil. The method of calculation is illustrated by application to: (1) The Joukowski airfoil in subsonic flow; and (2) the thin elliptic cone in supersonic flow. A general formula for the edge force is provided which is applicable to a variety of wing forms.
    Schlagwort(e): AERODYNAMICS
    Materialart: Collected Works of Robert T. Jones; p 533-538
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  • 16
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    The use of conical and cylindrical fields in supersonic wing theory (1976)
    In:  CASI
    Details
    Publikationsdatum: 2010-11-08
    Beschreibung: Some of the recent advances in the theory of thin airfoils are presented with particular reference to extensions of the theory to three dimensional flows and to supersonic speeds. The problem discussed herein is the calculation of the small disturbance velocities u, v, and w in the external field produced by the flight velocity V of the airfoil.
    Schlagwort(e): AERODYNAMICS
    Materialart: Collected Works of Robert T. Jones; p 483-497
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  • 17
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    Transonic/supersonic inlet R and D past, present, and future (1977)
    In:  CASI
    Details
    Publikationsdatum: 2004-10-07
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA Lewis Research Center Inlet Workshop; p 427-480
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  • 18
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    Address by james e. webb, administrator, national aeronautics and space administration (1963)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-01
    Beschreibung: Nasa achievements & international cooperation in space
    Schlagwort(e): AERODYNAMICS
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  • 19
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    Instruction ma-8 press kit mgws release no. 62-201 (1963)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-01
    Beschreibung: Mission plan of mercury-atlas 8 six-orbit flight of walter shirra in sigma 7 spacecraft
    Schlagwort(e): AERODYNAMICS
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  • 20
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    INTERNATIONAL COOPERATION IN SPACE (1962)
    In:  CASI
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    Publikationsdatum: 2009-11-17
    Beschreibung: Space science - international cooperation in space exploration
    Schlagwort(e): AERODYNAMICS
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  • 21
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    American progress and goals in space news release (1964)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Nasa program - progress and goals in space
    Schlagwort(e): AERODYNAMICS
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  • 22
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    The new age of discovery news release (1964)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: New age of discovery - space exploration and environment, lunar orbit and landing, and apollo spacecraft
    Schlagwort(e): AERODYNAMICS
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  • 23
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    Dedication of the hall of science, world's fair, new york city, new york, september 9, 1964 news release (1964)
    In:  CASI
    Details
    Publikationsdatum: 2006-10-26
    Beschreibung: Significance of hall of science, new york city, in understanding scientific disciplines - dedication remarks
    Schlagwort(e): AERODYNAMICS
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  • 24
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    Address by james e. webb, administrator, national aeronautics and space administration midwest governors' conference, minneapolis, minnesota, september 10, 1964 news release (1964)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Solving economic problems of midwest through joint efforts of industries and universities as related to nasa programs
    Schlagwort(e): AERODYNAMICS
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  • 25
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    Regulation in orbit- administrative aspects of the communications satellite act of 1962 (1964)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Regulation in orbit - administrative aspects of communications satellite act and space law
    Schlagwort(e): AERODYNAMICS
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  • 26
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    Some international aspects of communications satellite systems (1964)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Problems of space law and policy resulting from communications satellite act and inherent in operating satellite system
    Schlagwort(e): AERODYNAMICS
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  • 27
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    International organization and space (1964)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Capacity of organizations of international cooperation to develop and exert influence in field of space law
    Schlagwort(e): AERODYNAMICS
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  • 28
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    Monopoly and antitrust aspects of communications satellite operations (1964)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Monopoly and antitrust aspects of communications satellite operations - space law
    Schlagwort(e): AERODYNAMICS
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  • 29
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    The emerging customary law of space (1964)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Clarification of emergence of customary policies about space, and possibility of codification into space law
    Schlagwort(e): AERODYNAMICS
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  • 30
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    The 'freedom' of outer space- some problems of sovereignty, control, and jurisdiction (1964)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Freedom of outer space, boundary between nationally controlled airspace and free space, and problems of control, sovereignty, & jurisdiction
    Schlagwort(e): AERODYNAMICS
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  • 31
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    Remarks by james e. webb, administrator, national aeronautics and space administration, during langley inspection week at langley research center, hampton, virginia (1964)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Research and technology at nasa facility
    Schlagwort(e): AERODYNAMICS
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  • 32
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    A review of nasa's new scientific and technical information programs (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Information storage, retrieval, and dissemination for nasa program - data processing
    Schlagwort(e): AERODYNAMICS
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  • 33
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    Organizing for the conquest of space news release (1962)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Organization of nasa and office of manned space flight to accomplish exploration of space
    Schlagwort(e): AERODYNAMICS
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  • 34
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    Impact of nasa program on industry news release (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Challenge of space research & development program and impact on government, industry, & universities
    Schlagwort(e): AERODYNAMICS
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  • 35
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    Statement of dr. robert c. seamans, jr., associate administration, before the committee on science and astronautics, house of representives (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: General description of nasa programs and centers
    Schlagwort(e): AERODYNAMICS
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  • 36
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    Results of the space science program (1962)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Satellite space probes for properties and solar effect on earth atmosphere
    Schlagwort(e): AERODYNAMICS
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  • 37
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    Perspective and objectives of our national space program (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Socioeconomic problems arising from advances in science & technology and the space program
    Schlagwort(e): AERODYNAMICS
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  • 38
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    Goals and potentials of scientific research in space (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Space science & engineering and the space program
    Schlagwort(e): AERODYNAMICS
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  • 39
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    Implications of the space effort for science and technology (1963)
    In:  CASI
    Details
    Publikationsdatum: 2006-10-26
    Beschreibung: Space technology, the space program, and socio- economic problems of metropolitan areas
    Schlagwort(e): AERODYNAMICS
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  • 40
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    Space- the challenge and the promise news release (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Contributions of new mexico to space program
    Schlagwort(e): AERODYNAMICS
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  • 41
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    Administration and the conquest of space news release (1962)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Administrative aspects of space research and exploration
    Schlagwort(e): AERODYNAMICS
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  • 42
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    Role of higher education in our nation's future news release (1962)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Role of higher education in united states future
    Schlagwort(e): AERODYNAMICS
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  • 43
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    MEMORANDUM OF UNDERSTANDING BETWEEN THE FEDERAL COMMUNICATIONS COMMISSION AND THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION RELEASE 61-31 (1961)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Schlagwort(e): AERODYNAMICS
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  • 44
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    SPACE PROGRAM PROGRESS IN THE UNITED STATES (1961)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Schlagwort(e): AERODYNAMICS
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  • 45
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    A REPORT ON SPACE (1960)
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    Publikationsdatum: 2006-10-26
    Schlagwort(e): AERODYNAMICS
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  • 46
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    NATIONAL SPACE PROGRAM STATUS (1962)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Schlagwort(e): AERODYNAMICS
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  • 47
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    GEORGE WASHINGTON UNIVERSITY COMMENCEMENT ADDRESS, JUNE 7, 1961 (1961)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Schlagwort(e): AERODYNAMICS
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  • 48
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    INTERNATIONAL RELATIONS AND SPACE (1961)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Schlagwort(e): AERODYNAMICS
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  • 49
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    ADDRESS AT THE CHAMBER OF COMMERCE DINNER SALT LAKE CITY, UTAH SEPTEMBER 29, 1961 (1961)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Schlagwort(e): AERODYNAMICS
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  • 50
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    ADDRESS- THE CREATION OF A GOOD RESEARCH ENVIRONMENT (1961)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Schlagwort(e): AERODYNAMICS
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  • 51
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    Hypersonic flight simulation- aerodynamics (1964)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Laboratory simulation of aerodynamics of full-scale hypersonic flight
    Schlagwort(e): AERODYNAMICS
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  • 52
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    SPEECH BY HUGH I. DRYDEN, DEPUTY ADMINISTRATOR, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION BEFORE THE DISTRICT CONVENTION OF THE AMERICAN LEGION, DEPARTMENT OF VIRGINIA, ROANOKE, VIRGINIA, JULY 27, 1963 (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: U.s. space program summary
    Schlagwort(e): AERODYNAMICS
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  • 53
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    SOUNDING ROCKET MANAGEMENT AND ADMINISTRATION (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Sounding rocket management
    Schlagwort(e): AERODYNAMICS
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  • 54
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    NASA PROCUREMENT POLICIES (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Nasa procurement policies for contractors
    Schlagwort(e): AERODYNAMICS
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  • 55
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    HOW NASA SELECTS AND MANAGES PROGRAMS (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Nasa selection and management of programs
    Schlagwort(e): AERODYNAMICS
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  • 56
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    THE PRIME CONTRACTOR'S ROLE IN THE NATIONAL SPACE PROGRAM (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Prime contractors role in national space program - nasa
    Schlagwort(e): AERODYNAMICS
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  • 57
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    THE ECONOMIC EFFECTS OF THE SPACE PROGRAM (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Economic effect of space program - nasa
    Schlagwort(e): AERODYNAMICS
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  • 58
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    PATENT POLICY FOR COMMUNICATIONS SATELLITES- A UNIQUE VARIATION (1962)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Patent rights for communications satellites - nasa policy
    Schlagwort(e): AERODYNAMICS
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  • 59
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    THE NASA PROGRAM OF INDUSTRIAL APPLICATIONS (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Nasa program of industrial applications
    Schlagwort(e): AERODYNAMICS
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  • 60
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    ADDRESS BY (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: United states space program - launch vehicles, satellites and spacecraft
    Schlagwort(e): AERODYNAMICS
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  • 61
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    SCIENCE IN SPACE (1962)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Science in space
    Schlagwort(e): AERODYNAMICS
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  • 62
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    FREE ENTERPRISE IN SPACE (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Free enterprise in space - development of commercial space communication - nasa program
    Schlagwort(e): AERODYNAMICS
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  • 63
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    INTERNATIONAL COOPERATION IN SPACE EXPLORATION (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: International cooperation in space exploration - nasa program
    Schlagwort(e): AERODYNAMICS
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  • 64
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    UNIVERSITY RESEARCH ACTIVITIES AND THEIR IMPACT ON THE NATIONAL SPACE PROGRAM (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: University research activities and impact on national space program
    Schlagwort(e): AERODYNAMICS
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  • 65
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    IS THERE A FUTURE FOR SMALL BUSINESS IN THE SPACE AGE (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Future of small business in space age progress - nasa program
    Schlagwort(e): AERODYNAMICS
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  • 66
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    CONTRIBUTIONS OF EDUCATIONAL AND RESEARCH PROGRAMS TO MANPOWER AND ADVANCES IN THE SPACE SCIENCES (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Contribution of educational and research programs to manpower and advances in space science - nasa program
    Schlagwort(e): AERODYNAMICS
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  • 67
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    AFTER NOW, WHAT THEN IN SPACE QUES (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Space sciences for interplanetary travel - space radiation, satellites and extraterrestrial life
    Schlagwort(e): AERODYNAMICS
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  • 68
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    THE ROLE OF ENGINEERING IN THE SPACE PROGRAM (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Role of engineering in space program
    Schlagwort(e): AERODYNAMICS
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  • 69
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    FORCASTING TEN YEARS OF PROGRESS IN SPACE EXPLORATION (1963)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Space exploration - meteorological and communication satellites - mercury and apollo project
    Schlagwort(e): AERODYNAMICS
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  • 70
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    ADDRESS BY (1962)
    In:  CASI
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    Publikationsdatum: 2006-10-26
    Beschreibung: Nasa programs - general success factors involved
    Schlagwort(e): AERODYNAMICS
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  • 71
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    COMMUNICATIONS SATELLITES AND TELEPHONE RATES- PROBLEMS OF GOVERNMENT REGULATION (1961)
    In:  CASI
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    Publikationsdatum: 2008-08-25
    Beschreibung: Communications satellites and telephone rates, problems of government regulation
    Schlagwort(e): AERODYNAMICS
    Materialart: RM-2845-NASA
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  • 72
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    PUBLICATIONS OF THE JET PROPULSION LABORATORY, JULY 1960 THROUGH JUNE 1961 (1961)
    In:  CASI
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    Publikationsdatum: 2008-08-25
    Beschreibung: Publications of the jet propulsion laboratory
    Schlagwort(e): AERODYNAMICS
    Materialart: JPL-BIBL-39-2
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  • 73
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    Comments on wind-tunnel-flight correlations for the F-8 supercritical wing configurations (1977)
    In:  CASI
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    Publikationsdatum: 2004-12-03
    Schlagwort(e): AERODYNAMICS
    Materialart: Supercritical Wing Technol.: A Report on Flight Evaluation; p 111-120
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  • 74
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    BRIEFING FOR THE SOCIETY OF BUSINESS MAGAZINE EDITORS JAN. 28, 1961 (1961)
    In:  CASI
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    Publikationsdatum: 2006-03-16
    Schlagwort(e): AERODYNAMICS
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  • 75
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    NASA ANNOUNCES AGREEMENT WITH THE SOVIET ACADEMY OF SCIENCES ON IMPLEMENTATION OF COOPERATIVE SPACE PROGRAM (1963)
    In:  CASI
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    Publikationsdatum: 2006-03-16
    Beschreibung: International cooperative space program
    Schlagwort(e): AERODYNAMICS
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  • 76
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    ADDRESS BY COLONEL R. P. YOUNG, EXECUTIVE OFFICER NATIONAL AERONAUTICS AND SPACE ADMINISTRATION, AT THE INLAND EMPIRE WATERWAYS ASSOCIATED CONVENTION SEATTLE, WASHINGTON (1962)
    In:  CASI
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    Publikationsdatum: 2006-03-16
    Schlagwort(e): AERODYNAMICS
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  • 77
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    NASA CONTRACTS FOR ABSTRACTING SERVICE (1963)
    In:  CASI
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    Publikationsdatum: 2006-03-16
    Schlagwort(e): AERODYNAMICS
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  • 78
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    A parametric experimental study of the slotted-wall boundary condition (1978)
    In:  CASI
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    Publikationsdatum: 2006-02-22
    Beschreibung: An experimental study of slotted upper and lower walls in a two dimensional transonic wind tunnel with solid sidewalls is reported. Results are presented for several slot spacings and slot openness ratios. The experimental data were pressure measurements which were made on an airfoil model and on a sidewall near one of the slotted walls. The slotted-wall boundary condition coefficient, which related the pressure and streamline curvature near the wall, was determined from the wall pressure measurements. The measured wall-induced interference was correlated with the experimental values for the boundary condition coefficient. This correlation was compared with theory.
    Schlagwort(e): AERODYNAMICS
    Materialart: Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 459-471
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  • 79
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    In-flight lift and drag measurements on a first generation jet transport equipped with winglets (1982)
    In:  CASI
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    Publikationsdatum: 2006-02-14
    Beschreibung: A KC-135A aircraft equipped with wing tip winglets was flight tested to demonstrate and validate the potential performance gain of the winglet concept as predicted from analytical and wind tunnel data. Flight data were obtained at cruise conditions for Mach numbers of 0.70, 0.75, and 0.80 at a nominal altitude of 36,000 ft. and winglet configurations of 15 deg cant/-4 deg incidence, 0 deg cant/-4 deg incidence, and baseline. For the Mach numbers tested the data show that the addition of winglets did not affect the lifting characteristics of the wing. However, both winglet configurations showed a drag reduction over the baseline configuration, with the best winglet configuration being the 15 deg cant/-4 deg incidence configuration. This drag reduction due to winglets also increased with increasing lift coefficient. It was also shown that a small difference exists between the 15 deg cant/-4 deg incidence flight and wind tunnel predicted data. This difference was attributed to the pillowing of the winglet skins in flight which would decrease the winglet performance.
    Schlagwort(e): AERODYNAMICS
    Materialart: KC-135 Winglet Program Rev.; p 103-116
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  • 80
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    KC-135 winglet program overview (1982)
    In:  CASI
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    Publikationsdatum: 2006-02-14
    Beschreibung: A joint NASA/USAF program was conducted to accomplish the following objectives: (1) evaluate the benefits that could be achieved from the application of winglets to KC-135 aircraft; and (2) determine the ability of wind tunnel tests and analytical analysis to predict winglet characteristics. The program included wind-tunnel development of a test winglet configuration; analytical predictions of the changes to the aircraft resulting from the application of the test winglet; and finally, flight tests of the developed configuration. Pressure distribution, loads, stability and control, buffet, fuel mileage, and flutter data were obtained to fulfill the objectives of the program.
    Schlagwort(e): AERODYNAMICS
    Materialart: KC-135 Winglet Program Rev.; p 1-46
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  • 81
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    KC-135 wing and winglet flight pressure distributions, loads, and wing deflection results with some wind tunnel comparisons (1982)
    In:  CASI
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    Publikationsdatum: 2006-02-14
    Beschreibung: A full-scale winglet flight test on a KC-135 airplane with an upper winglet was conducted. Data were taken at Mach numbers from 0.70 to 0.82 at altitudes from 34,000 feet to 39,000 feet at stabilized flight conditions for wing/winglet configurations of basic wing tip, 15/-4 deg, 15/-2 deg, and 0/-4 deg winglet cant/incidence. An analysis of selected pressure distribution and data showed that with the basic wing tip, the flight and wind tunnel wing pressure distribution data showed good agreement. With winglets installed, the effects on the wing pressure distribution were mainly near the tip. Also, the flight and wind tunnel winglet pressure distributions had some significant differences primarily due to the oilcanning in flight. However, in general, the agreement was good. For the winglet cant and incidence configuration presented, the incidence had the largest effect on the winglet pressure distributions. The incremental flight wing deflection data showed that the semispan wind tunnel model did a reasonable job of simulating the aeroelastic effects at the wing tip. The flight loads data showed good agreement with predictions at the design point and also substantiated the predicted structural penalty (load increase) of the 15 deg cant/-2 deg incidence winglet configuration.
    Schlagwort(e): AERODYNAMICS
    Materialart: KC-135 Winglet Program Rev.; p 47-102
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  • 82
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    Status of advanced airfoil tests in the Langley 0.3-meter transonic cryogenic tunnel (1984)
    In:  CASI
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    Publikationsdatum: 2006-02-14
    Beschreibung: A joint NASA/U.S. industry program to test advanced technology airfoils in the Langley 0.3-meter Transonic Tunnel (TCT) was formulated under the Langley ACEE Project Office. The objectives include providing U.S. industry an opportunity to compare their most advanced airfoils to the latest NASA designs by means of high Reynolds number tests in the same facility. At the same time, industry would again experience in the design and construction of cryogenic test techniques. The status and details of the test program are presented. Typical aerodynamic results obtained, to date, are presented at chord Reynolds number up to 45 x 10(6) and are compared to results from other facilities and theory. Details of a joint agreement between NASA and the Deutsche Forschungs- und Versuchsantalt fur Luft- and Raumfahrt e.V. (DFVLR) for tests of two airfoils are also included. Results of these tests will be made available as soon as practical.
    Schlagwort(e): AERODYNAMICS
    Materialart: Advan. Aerodyn.: Selected NASA Res.; p 37-53
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  • 83
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    ADDRESS BY JAMES E. WEBB, ADMINISTRATOR, 〈TO THE〈 EXPLORERS CLUB, WALDORF ASTORIA HOTEL, NEW YORK CITY, NOV. 2, 1962 (1962)
    In:  CASI
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    Publikationsdatum: 2006-03-16
    Schlagwort(e): AERODYNAMICS
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  • 84
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    A procedure for analyzing transonic flow over harmonically oscillating airfoils (1978)
    In:  CASI
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    Publikationsdatum: 2006-02-22
    Beschreibung: Finite difference procedures were successfully used to solve the steady transonic flow about airfoils and appear to provide a practical means for calculating the corresponding unsteady flow. The purpose of the paper is to describe a finite difference procedure derived from the equations for the potential flow by assuming small perturbations and harmonic motion. The velocity potential is divided into steady and unsteady parts, and the resulting unsteady equation is linearized on the basis of small amplitudes of oscillation. The steady velocity potential, which must be calculated first, is described by the classical nonlinear transonic differential equation.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 657-670
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  • 85
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    Section drag coefficients from pressure probe transverses of a wing wake at low speeds (1978)
    In:  CASI
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    Publikationsdatum: 2006-02-22
    Beschreibung: An in-flight wing wake section drag investigation was conducted using traversing pitot and static probes. The primary objective was to develop measurement techniques and improve the accuracy of in-flight wing profile drag measurements for low values of dynamic pressure and Reynolds number. Data were obtained on a sailplane for speeds from about 40 knots to 125 knots at chord Reynolds numbers between 1,000,000 and 3,000,000. Tests were conducted with zero flap deflection, deflected flaps, and various degrees of surface roughness, and for smooth and rough atmospheric conditions. Several techniques were used to increase data reliability and to minimize certain bias errors. A discussion of the effects of a total pressure probe in a pressure gradient, and the effects of discrete turbulence levels, on the data presented and other experimental results is also included.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 601-621
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  • 86
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    Some calculations of transonic potential flow for the NACA 64A006 airfoil with oscillating flap (1978)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-22
    Beschreibung: A method for calculating the transonic flow over steady and oscillating airfoils was developed by Isogai. It solves the full potential equation with a semi-implicit, time-marching, finite difference technique. Steady flow solutions are obtained from time asymptotic solutions for a steady airfoil. Corresponding oscillatory solutions are obtained by initiating an oscillation and marching in time for several cycles until a converged periodic solution is achieved. In this paper the method is described in general terms, and results are compared with experimental data for both steady flow and for oscillations at several values of reduced frequency. Good agreement for static pressures is shown for subcritical speeds, with increasing deviation as Mach number is increased into the supercritical speed range. Fair agreement with experiment was obtained at high reduced frequencies with larger deviations at low reduced frequencies.
    Schlagwort(e): AERODYNAMICS
    Materialart: Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 689-700
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  • 87
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    Applications of dynamic measurement techniques to wind-tunnel testing (1978)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-22
    Beschreibung: The uses of laser Doppler velocimeter, hot wire, and surface hot film techniques in the study of turbulent flows are described, and data obtained in compressible flows are discussed. Applications are illustrated with measurements of wind tunnel freestream turbulence characteristics and with data obtained in transitional, turbulent, and separated shear flows. A new method which was developed for the study of time dependent and unsteady turbulent flows is also presented.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 571-588
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  • 88
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    Component testing for dynamic model verification (1984)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Dynamic model verification is the process whereby an analytical model of a dynamic system is compared with experimental data, adjusted if necessary to bring it into agreement with the data, and then qualified for future use in predicting system response in a different dynamic environment. These are various ways to conduct model verification. The approach taken here employs Bayesian statistical parameter estimation. Unlike curve fitting, whose objective is to minimize the difference between some analytical function and a given quantity of test data (or curve), Bayesian estimation attempts also to minimize the difference between the parameter values of that funciton (the model) and their initial estimates, in a least squares sense. The objectives of dynamic model verification, therefore, are to produce a model which: (1) is in agreement with test data; (2) will assist in the interpretation of test data; (3) can be used to help verify a design; (4) will reliably predict performance; and (5) in the case of space structures, will facilitate dynamic control.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center Recent Experiences in Multidisciplinary Analysis and Optimization, Part 2; 15 p
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  • 89
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    Post and a random-walk search mode (1984)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Multidisciplinary analysis often requires optimization of nonlinear systems that are subject to constraints. Trajectory optimization is one example of this situation. The Program to Optimize Simulated Trajectories (POST) was used successfully for a number of problems. The purpose is to describe POST and a new optimization approach that has been incorporated into it. Typical uses of POST will also be illustrated. The projected-gradient approach to optimization is the preferred option in POST and is discussed. A new approach to optimization, the random-walk approach, is described, and results with the random-walk approach are presented.
    Schlagwort(e): AERODYNAMICS
    Materialart: Recent Experiences in Multidisciplinary Analysis and Optimization, Part 2; 23 p
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  • 90
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    Wall interference measurements for three-dimensional models in transonic wind tunnels: Experimental difficulties (1984)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The purpose is not to provide a detailed discussion of several wall interference experiments, but rather to use these experiments (recently accomplished in the Boeing Transonic Wind Tunnel (BTWT) to illustrate the problems associated with many of the measurements required by current wall interference assessment/correction (WIAC) procedures. The wall correction to lift is emphasized. It is shown that, because conventional tunnels and relatively small models continue to be used, the flow field or flow boundary measurements to be made impose severe requirements on the experiment itself. In some cases, existing instrumentation and test techniques may not be adequate to obtain the data accuracies needed.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 21-42
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  • 91
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    Adaptation of a four-wall interference assessment/correction procedure for airfoil tests in the 0.3-m TCT (1984)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Based upon limited, initial observations of wall interference corrections obtained for one airfoil test, there is a need for assessing the upstream flow direction. If there is no direct measurement then a two-pass correction procedure similar to the one described here is required. Questions have arisen pertaining to the correct interpretation of the pressure coefficients measured on the slats of a slotted tunnel wall, the interpretation of just what the calculated equivalent body encompasses or should include, and what can or should be considered as quantitative criteria for data correctability. Further studies using this modified procedure will address these questions. Hopefully, a meaningful WIAC procedure can be validated for the airfoil tests in the 0.3-m TCT.
    Schlagwort(e): AERODYNAMICS
    Materialart: Wind Tunnel Wall Interference Assessment and Correction, 1983; p 393-414
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  • 92
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    Some experience with Barnwell-Sewall type correction to two-dimensional airfoil data (1984)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: A series of airfoils were tested in the Langley 0.3-Meter Transonic Cryogenic Tunnel (TCT) at Reynolds numbers from 2 to 50 million. The 0.3-m TCT is equipped with Barnwell slots designed to minimize blockage due to the tunnel flow and ceiling. This design suggests that sidewall corrections for blockage is needed, and that a lifting airfoil produces a change in angle of attack. Sidewall correction methods were developed for subsonic and subsonic-transonic flow. Comparisons of theory with experimental data obtained in the 0.3-m TCT for two airfoils, the British NPL 9510 and the German R-4 are presented. The NPL 9510 was tested as part of the NASA/United Kingdom Joint Aeronautical Program and R-4 was tested as part f the DFVLR/NASA Advanced Airfoil Research Program. For the NPL 9510 airfoil, only those test points that one would anticipate being difficult to predict theoretically are presented.
    Schlagwort(e): AERODYNAMICS
    Materialart: Wind Tunnel Wall Interference Assessment and Correction, 1983; p 375-392
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  • 93
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    Experiences with a high-blockage model tested in the NASA Ames 12-foot pressure wind tunnel (1984)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Representation of the flow around full-scale ships was sought in the subsonic wind tunnels in order to a Hain Reynolds numbers as high as possible. As part of the quest to attain the largest possible Reynolds number, large models with high blockage are used which result in significant wall interference effects. Some experiences with such a high blockage model tested in the NASA Ames 12-foot pressure wind tunnel are summarized. The main results of the experiment relating to wind tunnel wall interference effects are also presented.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 345-360
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  • 94
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    An inerference assessment approach for a three-dimensional slotted tunnel with sparse wall pressure data (1984)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The various procedures referred to as wall interference assessment and correction procedures presume the existence of a surface distribution of data (usually static pressure) measured over a surface on or near the tunnel walls for each test point to be assessed. An alternative approach in which a reasonably sophisticated computer model of the test section flow would be fitted parametrically to a sparse set of measured data is presented. The measurements provides line distributions of static pressure near the center lines of the top, side and bottom walls. The development of a test section model incorporating explicit recognition of discrete slots of finite length with controlled flow reentry into the solid wall downstream portion of the tunnel is shown.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Research Center. Wind Tunnel Wall Interference Assessment and Correction, 1983; p 323-334
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  • 95
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    Aircraft (1977)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-16
    Beschreibung: The physical principles of flight, and the consideration of atmospheric composition and aerodynamic forces in the design and construction of various types of aircraft are discussed. Flight characteristics are described for helicopters, rotary-wing aircraft, short and vertical takeoff aircraft, and tailess or variable geometry wing aircraft. Flow characteristics at various speeds are also discussed.
    Schlagwort(e): AERODYNAMICS
    Materialart: Soviet Aircraft and Rockets (NASA-TT-F-770); p 24-80
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  • 96
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    Executive summary of Aircraft Icing Specialists Workshop (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: In a period of escalating development costs for new aircraft, there is growing interest in a renewed and coordinated icing research effort to achieve an updating or modernization of each aspect of the technological issues that are involved. This includes the data base, analysis methods, test techniques, and test facilities.
    Schlagwort(e): AERODYNAMICS
    Materialart: Aircraft Icing; p 1-16
    Format: text
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  • 97
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    Safety hazard of aircraft icing (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: The problem of aircraft icing is reported as well as the type of aircraft affected, the pilots involved, and an identification of the areas where reduction in icing accidents are readily accomplished.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Lewis Res. Center Aircraft Icing; p 21-27
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  • 98
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    The lateral flying qualities of the Bell XP-77 airplane as estimated from full-scale tunnel tests, 16 June 1944 (1976)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-16
    Beschreibung: Results are presented for tests made of the full scale model of the airplane in the NACA full scale tunnel. These tests were planned so as to cover as completely as possible the lateral flying quality requirements for pursuit-type airplanes contracted for by the United States Army Air Forces.
    Schlagwort(e): AERODYNAMICS
    Materialart: Collected Works of Charles J. Donlan; 23 p
    Format: text
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  • 99
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    Civil Helicopter icing problems (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: The ice capabilities of rotary wing aircraft are examined. Recommendations are given to improve the inadequacies of the weather forecasts pertaining to ice, and to adopt a low maintenance anti-ice system.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Lewis Res. Center Aircraft Icing; p 29-30
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  • 100
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    Overview of helicopter ice protection system developments (1979)
    In:  CASI
    Details
    Publikationsdatum: 2006-01-12
    Beschreibung: Helicopter ice protection design criteria was developed and technological shortcoming in meeting helicopter mission requirements is that of helicopter rotor blade ice protection. Airframe components are protected using existing technology while the rotor blade protected using the cyclic electrothermal deicing concept.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Lewis Res. Center Aircraft Icing; p 39-65
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