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  • AERODYNAMICS  (3,391)
  • Fluid Mechanics and Thermodynamics
  • 2020-2020
  • 1975-1979  (2,121)
  • 1970-1974  (1,260)
  • 1945-1949  (69)
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  • 1
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    Economy of flight at supersonic speeds (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 499-514
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  • 2
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    Aeroelastic characteristics of an oblique wing (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 867-883
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  • 3
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    Aerodynamic design for supersonic speeds (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 625-644
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  • 4
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    Theoretical determination of the minimum drag of airfoils at supersonic speeds (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 567-578
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  • 5
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    The minimum drag of thin wings in frictionless flow (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 557-565
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  • 6
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    Calculation of the motion of an airplane under the influence of irregular disturbances (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 21-29
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  • 7
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    Three-dimensional wings of minimum pressure drag (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: 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.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Res. Center Collected Works of Robert T. Jones; p 645-656
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  • 8
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    Some recent developments in the aerodynamics of wings for high speeds (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 601-608
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  • 9
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    Theoretical correction for the lift of elliptic wings (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 245-249
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  • 10
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    Reduction of wave drag by antisymmetric arrangement of wings and bodies (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 657-664
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  • 11
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    The compressibility rule for drag of airfoil noses (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 619-623
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  • 12
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    Possibilities of efficient high-speed transport airplanes (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 579-592
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  • 13
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    Leading-edge singularities in thin-airfoil theory (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 533-538
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  • 14
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    The use of conical and cylindrical fields in supersonic wing theory (1976)
    In:  CASI
    Details
    Publication Date: 2010-11-08
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 483-497
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  • 15
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    Transonic/supersonic inlet R and D past, present, and future (1977)
    In:  CASI
    Details
    Publication Date: 2004-10-07
    Keywords: AERODYNAMICS
    Type: NASA Lewis Research Center Inlet Workshop; p 427-480
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  • 16
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    Application of advanced aerodynamics to future transport aircraft (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Applications of supercritical airfoils to transport aircraft designs
    Keywords: AERODYNAMICS
    Type: NASA AIRCRAFT SAFETY AND OPERATING PROBL., VOL. 1 1971; P 165-176
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  • 17
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    Aircraft response to the wing trailing vortices generated by large jet transports (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Flight tests for evaluating effect of wing-tip vortex wake generated by large jet transports on smaller aircraft
    Keywords: AERODYNAMICS
    Type: NASA AIRCRAFT SAFETY AND OPERATING PROBL., VOL. 1 1971; P 115-126
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  • 18
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    Progress report on wing-trailing-vortex studies (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Effect of wing-tip vortex wakes generated by large jet transport aircraft on smaller airplanes
    Keywords: AERODYNAMICS
    Type: NASA AIRCRAFT SAFETY AND OPERATING PROBL., VOL. 1 1971; P 101-113
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  • 19
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    Gust alleviation (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Alleviation of lateral and longitudinal gust effects on aircraft
    Keywords: AERODYNAMICS
    Type: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 505-553
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  • 20
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    Effects of aeroelasticity on static aerodynamic derivatives (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Effects of aeroelasticity on static longitudinal aerodynamic derivatives
    Keywords: AERODYNAMICS
    Type: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 375-438
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  • 21
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    Design of bodies for low drag and high performance in practical hypersonic flight (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Minimizing drag and increasing performance of optimum shapes at hypersonic flight
    Keywords: AERODYNAMICS
    Type: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 103-174
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  • 22
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    Methods of obtaining stability derivatives (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Least squares method and iteration technique for obtaining aerodynamic stability derivatives
    Keywords: AERODYNAMICS
    Type: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 71-101
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  • 23
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    Analysis of the flow field of a jet in a subsonic crosswind (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Jet induced flow field effects on V/STOL aircraft in subsonic transition flight
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 683-702
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  • 24
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    Procedures for designing supersonic bodies of revolution from prescribed surface pressure distributions (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Iterative method for designing supersonic body of revolution from surface pressure distribution
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 75-84
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  • 25
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    Ground-wind-load considerations for space shuttle vehicles (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Ground wind loads on reusable space shuttles
    Keywords: AERODYNAMICS
    Type: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 143-160
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  • 26
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    Buffet and aerodynamic noise (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Space shuttle buffeting and aerodynamic noise
    Keywords: AERODYNAMICS
    Type: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 238-247
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  • 27
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    Theoretical investigation of ducted fan interference for transport-type aircraft (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Ducted fan interference analysis for transport aircraft
    Keywords: AERODYNAMICS
    Type: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 703-719
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  • 28
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    Time-dependent numerical method for treating complicated blunt-body flow fields (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Time-dependent numerical method for blunt body flow field solutions
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 177-195
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  • 29
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    A critical evaluation of analytic methods for predicting laminar-boundary-layer shock-wave interaction (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Prediction methods for boundary layer and flow field characteristics in shock wave-boundary layer interaction
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 515-539
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  • 30
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    A numerical method for computing three-dimensional viscous supersonic flow fields about slender bodies (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Numerical analysis of three dimensional viscous supersonic flow fields about slender bodies
    Keywords: AERODYNAMICS
    Type: NASA, WASHINTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 265-321
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  • 31
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    In-flight aeroacoustic environments on prospective space shuttle vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The problem of in-flight aerodynamic noise has been studied by reliable estimates of full scale surface-pressure fluctuations from scale model tests in wind tunnels. Scaling relationships have been verified, and many details of the fluctuating pressure characteristics such as spatial correlation and convection velocities are understood. The effects of the wind tunnel environmental turbulence and noise have also been investigated sufficiently so that threshold levels of usable data are known.
    Keywords: AERODYNAMICS
    Type: NASA Space Shuttle Technol. Conf.; p 71-96
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  • 32
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    Optimization of supersonic inlets using the method of characteristics (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Method of characteristics for computerized design of optimal supersonic inlets
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 569-581
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  • 33
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    A new method for calculating near and far field pressure about arbitrary configurations (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Aerodynamic method of characteristics for pressure field calculations about wing-body combinations
    Keywords: AERODYNAMICS
    Type: L METHODS IN AIRCRAFT AERODYN. 1970; P 215-227
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  • 34
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    The analysis of propeller-wing flow interaction (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Numerical analysis of propeller-wing flow interaction with slipstreams
    Keywords: AERODYNAMICS
    Type: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 721-742
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  • 35
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    Wind tunnel simulation of ground wind shear and turbulence spectra with possible application to space shuttle launch problems (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Wind tunnel simulation of ground wind shear and turbulence spectra and application to space shuttle launching
    Keywords: AERODYNAMICS
    Type: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 161-175
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  • 36
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    Theoretical studies of vortex flow on slender wing-body combinations (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Lift and pressure distribution calculations for winged body with leading edge vortices
    Keywords: AERODYNAMICS
    Type: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 113-129
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  • 37
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    Finite-difference analysis of the compressible turbulent boundary layer on a blunt swept slab with leading-edge blowing (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Finite difference solution for compressible turbulent boundary layer equations of swept slab with leading edge blowing
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 417-472
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  • 38
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    Recent advances in research on compressible turbulent boundary layers (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Review of prediction methods for compressible turbulent boundary layers
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 355-416
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  • 39
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    An analysis of finite-difference techniques applied to equations governing convective transfer (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Finite difference analysis of hyperbolic partial differential equations
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 245-264
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  • 40
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    Prediction of supersonic and hypersonic inlet flow fields (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Computer programs for predicting flow field properties in supersonic and hypersonic inlets
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 583-595
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  • 41
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    Improvement of wing-body interference theory for hypersonic speeds (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Wing-body interference theory for calculating lift slope and stability at hypersonic speed
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 101-111
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  • 42
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    Some recent developments in subsonic lifting-surface theory (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Numerical lifting surface theory with spanwise distribution of control points
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 1-35
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  • 43
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    Application of the method of characteristics to noncircular bodies at angle of attack (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Method of characteristics for flow field analysis on elliptical winged body
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 159-176
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  • 44
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    The use of finite element methods for predicting the aerodynamics of wing-body combinations (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Finite element method for predicting aerodynamic characteristics of wing-body combinations
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 37-51
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  • 45
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    Potential flow solutions for inlets of VTOL lift fans and engines (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Potential flow solution for VTOL inlets in static and crossflow operation
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 659-681
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  • 46
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    Methods of analyzing propeller and rotor boundary layers with crossflow (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Analysis of secondary flow effects in propeller and rotor boundary layers
    Keywords: AERODYNAMICS
    Type: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 473-514
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  • 47
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    A new method for analysis of transonic flow (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Finite difference method for transonic flow solution in axial stator
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 597-621
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  • 48
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    A method for analyzing the interaction of an oblique shock wave and a boundary layer (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Method of characteristics for calculating oblique shock wave interaction with turbulent boundary layer
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 541-567
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  • 49
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    A critical evaluation of panel flutter aerodynamics (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Aerodynamic forces in supersonic panel flutter
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 335-353
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  • 50
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    An analysis of Coanda jet flows (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Static laminar Coanda jet flow around circular cylinder with external flow entrainment
    Keywords: AERODYNAMICS
    Type: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 197-214
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  • 51
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    Empirical method for estimating pressures on elliptic cones (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Correlation method for estimating pressure distribution over elliptic supersonic cones
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 85-99
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  • 52
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    Calculative techniques for transonic flows (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Calculation methods for predicting transonic aerodynamic characteristics of wing-body combinations
    Keywords: AERODYNAMICS
    Type: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 53-73
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  • 53
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    Flutter and unsteady lift theory (1971)
    In:  CASI
    Details
    Publication Date: 2009-11-16
    Description: Aeroelasticity and unsteady flow problems of aircraft
    Keywords: AERODYNAMICS
    Type: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 289-374
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  • 54
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    The relevance of recent advances in unsteady aerodynamics to the space shuttle program (1970)
    In:  CASI
    Details
    Publication Date: 2009-11-17
    Description: Prediction of steady and unsteady airloads on space shuttles
    Keywords: AERODYNAMICS
    Type: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 223-237
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  • 55
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    Comments on wind-tunnel-flight correlations for the F-8 supercritical wing configurations (1977)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 111-120
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  • 56
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    Summary and future plans (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 121-133
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  • 57
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    Piloting and operational aspets of the F-8 supercritical wing airplane (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 97-110
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  • 58
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    Status of the F-8 supercritical wing program (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 49-58
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  • 59
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    F-8 supercritical wing pressure distribution evaluation (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 71-84
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  • 60
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    Buffet characteristics of the F-8 supercritical wing airplane (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 85-96
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  • 61
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    The NASA supercritical airfoil and its application to swept wings (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 1-12
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  • 62
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    Evolution of the F-8 supercritical wing configuration (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 35-48
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  • 63
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    Preliminary lift and drag characteristics of the F-8 supercritical wing airplane (1973)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: its Supercritical Wing Technol.: A Report on Flight Evaluation; p 59-70
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  • 64
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    A parametric experimental study of the slotted-wall boundary condition (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 459-471
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  • 65
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    A procedure for analyzing transonic flow over harmonically oscillating airfoils (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: 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.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 657-670
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  • 66
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    Section drag coefficients from pressure probe transverses of a wing wake at low speeds (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: 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.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 601-621
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  • 67
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    Some calculations of transonic potential flow for the NACA 64A006 airfoil with oscillating flap (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 689-700
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  • 68
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    Applications of dynamic measurement techniques to wind-tunnel testing (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: 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.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 571-588
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  • 69
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    Aircraft (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Soviet Aircraft and Rockets (NASA-TT-F-770); p 24-80
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  • 70
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    Executive summary of Aircraft Icing Specialists Workshop (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Aircraft Icing; p 1-16
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  • 71
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    Safety hazard of aircraft icing (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: 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.
    Keywords: AERODYNAMICS
    Type: NASA. Lewis Res. Center Aircraft Icing; p 21-27
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  • 72
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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
    Publication Date: 2006-01-16
    Description: 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.
    Keywords: AERODYNAMICS
    Type: Collected Works of Charles J. Donlan; 23 p
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  • 73
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    Civil Helicopter icing problems (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: 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.
    Keywords: AERODYNAMICS
    Type: NASA. Lewis Res. Center Aircraft Icing; p 29-30
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  • 74
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    Overview of helicopter ice protection system developments (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: 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.
    Keywords: AERODYNAMICS
    Type: NASA. Lewis Res. Center Aircraft Icing; p 39-65
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  • 75
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    A review of the icing situation from the standpoint of general aviation (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: An overview of the present situation in the field of aircraft icing with respect to certification and operation of nontransport category airplanes is given. Problems of definition and inconsistencies are pointed out. Problems in the forecasting and measurement of icing intensities are discussed. The present regulatory environment is examined with respect to its applicability and appropriateness to nontransport airplanes.
    Keywords: AERODYNAMICS
    Type: NASA. Lewis Res. Center Aircraft Icing; p 31-38
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  • 76
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    Icing of aircraft Some remarks with an historical slant from a cloud physicist (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Three areas of interest are commented on: cloud physics, nowcasting, and instrumentation. A comparison is made of what was done 30 years ago to what might be done in light of developments in related areas of cloud physics, weather modification and instrumentation.
    Keywords: AERODYNAMICS
    Type: NASA. Lewis Res. Center Aircraft Icing; p 17-19
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  • 77
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    Computational aerodynamics (1975)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The application of computer techniques for solving Navier-Stokes equations in support of wind tunnel tests is discussed. The ILLIAC IV computer is considered for this purpose and its limitations are analyzed. The author states that improved computers will make it possible to solve many aerodynamic problems and reduce the amount of wind tunnel testing required for adequate data processing.
    Keywords: AERODYNAMICS
    Type: NASA/Univ. Conf. on Aeron.; p 211-212
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  • 78
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    On wake vortex alleviation (1975)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Research within NASA relating to the nature of lift-induced vortex wakes behind large aircraft and the means whereby the hazard they represent to smaller aircraft can be alleviated is reviewed. The research, carried out in ground based facilities and in flight shows that more rapid dispersion of the wake can be effected by several means and that the modification of span-loading by appropriate flap deflection holds promise of early practical application.
    Keywords: AERODYNAMICS
    Type: NASA/Univ. Conf. on Aeron.; p 143-168
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  • 79
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    EBF noise tests with engine under-the-wing and over-the-wing configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Noise tests of externally blown flaps with the engine under the wing and engine over the wing configurations were conducted. Flap noise data obtained on a TF-34 aircraft are discussed. Noise data obtained during a free-jet forward-speed-effect analysis are presented. Noise sources associated with upper surface flap blowing are described. Results of a small scale configuration screening study and some large scale model test data are analyzed. The noise data for the engine over wing configurations are compared with the engine under the wing configurations.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 455-473
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  • 80
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    Flap noise generation and control (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The characteristics of aerodynamic noise generated by the interaction of an airstream with a flap surface are discussed. The location and behavior of various noise sources were investigated to determine optimal quieting techniques. A schematic diagram of the jet-flap concepts being considered for integrated-powered-lift systems for short takeoff aircraft is shown. Each of the concepts has in common high velocity turbulent air flowing over relatively rigid surfaces with resultant production of interaction noise. The nature, location, and control of noise sources which involve the interactions of air flows with airfoil surfaces are examined.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 413-426
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  • 81
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    Acoustic characteristics of large-scale STOL models at forward speed (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Wind-tunnel investigations of the acoustic characteristics of the externally blown jet flap (EBF) and augmentor wing STOL concepts are discussed. The large-scale EBF model was equipped with a triple-slotted flap blown by four JT15D turbofan engines with circular, coannular exhaust nozzles. The large-scale augmentor wing model was equipped with an unlined augmentor blown by a slot primary nozzle. The effects of airspeed and angle of attack on the acoustics of the EBF were small. Flap deflection had a greater effect on the acoustics of the augmentor wing than did airspeed. The total sound power was also significantly higher for landing indicating that turning in the augmentor generated acoustic energy. Airspeed produced a small aft shift in acoustic directivity with no significant change in the peak perceived noise levels or sound power levels. Small-scale research of the acoustics for the augmentor wing has shown that by blowing an acoustically treated augmentor with a lobed primary nozzle, the 95-PNdb noise level goal can be achieved or surpassed.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 443-454
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  • 82
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    Externally blown flap impingement noise (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Tests of the noise produced by the impingement of the jet exhaust on the wing and flap for an externally blown flap system were conducted with a CF700 turbofan engine and an F-111B wing panel. The noise produced with a daisy nozzle installed on the engine was greater than that produced by a conical nozzle at the same thrust. The presence of the wing next to the test nozzles increased the noise, as did increasing the flap deflection angle. Compared with the conical nozzle, the daisy nozzle produced slightly less noise at a flap deflection of 60 deg but produced more noise at the lower flap deflections tested. Tests showed that the single-slotted flap deflected 60 deg, produced less noise than the double-slotted flaps. Also, maintaining the maximum distance between the exit nozzle and flap system resulted in a minor reduction in noise.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 427-441
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  • 83
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    Externally blown flap dynamic loads (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Some of the principal results obtained in three series of measurements of fluctuating surface pressures induced on externally blown flaps by jet impingment are presented. Large- and small-scale models and hot- and cold-flow tests are considered. The discussion sets forth scaling parameters and consistent features of the root-mean-square values and spectra of the loading. Implications of these results with regard to sonic fatigue are indicated.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 131-142
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  • 84
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    Survey of wing and flap lower-surface temperatures and pressures during full-scale ground tests of an externally blown flap system (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Full-scale ground tests of an externally blown flap system were made using the wing of an F-111B airplane and a CF700 engine. Pressure and temperature distributions were determined on the undersurface of the wing, vane, and flap for two engine exhaust nozzles (conical and daisy) at several engine power and engine/wing positions. The tests were made with no airflow over the wing. The leading-edge wing sweep angle was fixed at 26 deg, the angle of incidence between the engine and the wing was fixed at 3 deg, and the tests were conducted with the flap retracted, extended and deflected 35 deg, and extended and deflected 60 deg. The integrated local pressures on the undersurface of the flap produced loads approximately three times as great at the 60 deg flap position as at the 35 deg flap position. With both nozzle configurations, more than 90 percent of the integrated pressure loads were contained within plus or minus 20 percent of the flap span centered around the engine exhaust centerline. The maximum temperature recorded on the flaps was 218 C (424 F) for the conical nozzle and 180 C (356 F) for the daisy nozzle.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 143-156
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  • 85
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    Simulator evaluation of the flying qualities of externally blown flap and augmentor wing transport configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Concurrent simulations of powered-lift STOL transport aircraft having either an externally blown flap configuration or an augmentor wing configuration were conducted. The following types of simulators of varying sophistication were used: (1) a simple fixed-base simulation with a simple visual display, (2) a more complex fixed-base simulation using a realistic transport cockpit and a high-quality visual display, and (3) a six-degree-of-freedom motion simulator that had a realistic transport cockpit and a sophisticated visual display. The unaugmented flying qualities determined from these simulations were rated as unacceptable for both the externally blown flap and augmentor wing configurations. The longitudinal, lateral-directional, and single-engine-failure characteristics were rated satisfactory with extensive augmentation, including pitch and roll command systems, flight-path (or speed) augmentation, turn coordination, and effective yaw damping. However, the flare and landing characteristics from any approach glide-path angle in excess of 4 deg were rated as unsatisfactory but acceptable.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 157-800
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  • 86
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    Aerodynamics of the upper surface blow flap (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The results of some preliminary wind-tunnel investigations made to provide fundamental aerodynamic information on the upper surface blown jet-flap concept incorporating high-bypass-ratio turbofan engines are summarized. The results of the investigation have shown the concept to have aerodynamic performance generally similar to that of other externally blown high-lift systems. A few of the more critical problems associated with this concept have been identified and preliminary solutions to some of these problems have been found. These results have proven to be sufficiently encouraging to warrant continuation of fundamental research efforts on the concept.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center STOL Technol.; p 97-110
    Format: text
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  • 87
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    Advanced augmentor-wing research (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Results of research on advanced augmentors are discussed. Research concerned with performance has indicated that: (1) augmentors with lobe-type nozzles give higher thrust augmentation than those with slot-type primary nozzles, (2) the thrust of augmentor wings at forward speed is greater than that of internally blown flaps for the speed range of interest, and (3) the optimum augmentor geometry at forward speed may be different from the optimum static geometry. Analysis of augmentor-wing data has shown that the data may be correlated by accounting for the augmentation and entrainment in defining a net thrust coefficient.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 87-96
    Format: text
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  • 88
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    Aerodynamic characteristics of a swept augmentor wing (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: A brief outline of augmentor wing research sponsored by Ames Research Center is presented and is followed by a discussion of large-scale wind-tunnel test results for a swept augmentor wing configuration. The results showed that the augmentor wing could be applied to high-speed swept wing designs with little adverse effect on either the basic performance of the augmentor or the longitudinal characteristics, including maximum lift and stall. Three lateral control devices were shown to be effective and ground effect was measured for several complete aircraft configurations.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 71-86
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  • 89
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    Aerodynamic loads measurements on externally blown flap STOL models (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Small-scale-model data have shown large static loads on the flap system behind the engines. The large-scale-model tests confirmed the magnitude of these loads and indicated that the relative loading of each flap element depends on the engine-wing-flap geometry. Flap response measurements indicated that the unsteady pressure loading excited the natural vibration modes of the flap system on this model. Since this was a boilerplate model, the only conclusion that can be drawn is that the possibility of large vibration loads must be considered for a flight-weight structure. The similarity of the unsteady pressure and flap response spectra for the wind-off and wind-on cases indicated that it may be possible to realistically test flight-weight flap structures on a static test stand rather than endure the extra costs and scheduling problems associated with large-scale wind-tunnel tests. There is a potential flap-temperature problem which if not resolved might preclude the use of materials such as aluminum and the composites in the flap structure.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 121-130
    Format: text
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  • 90
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    Aerodynamic and performance characteristics of externally blown flap configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The application of externally blown flaps for improving the performance of short takeoff aircraft is discussed. The characteristics of externally blown flap powered lift are examined. A method for predicting the aerodynamic performance of a particular externally blown flap configuration is presented. The following specific effects are analyzed: (1) induced aerodynamics, (2) static turning, (3) flap span and deflection, and (4) engine size and chord flap.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 43-54
    Format: text
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  • 91
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    Stability and control of externally blown flap configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The results of wind-tunnel investigations on the stability and control characteristics of externally blown jet-flap configurations are presented. Conventional wind-tunnel tests and free-flight model tests have shown that longitudinal trim and stability can be achieved by a properly located horizontal tail of sufficient size, and that lateral trim in the engine-out condition can be produced by combinations of differential flap, spoiler, and rudder deflection. Free-flight model tests have revealed a lightly damped Dutch roll lateral oscillation, and have shown that the oscillation can be stabilized by use of artificial damping.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 55-70
    Format: text
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  • 92
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    Three dimensional boundary layer separation in supersonic flow (1976)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: An account is given of a detailed experimental investigation of three dimensional boundary layer separation in supersonic flow. In investigating three dimensional effects on supersonic separation, models were chosen which exhibited departures from two dimensional flow in the simplest way. The plane compression corner was replaced by a plate attached to a swept back wedge formed by two obliquely intersecting planes. Maintaining a constant tunnel Mach number of 2.5, surface pressure measurements were made on these models at static orifices spaced along the centerline and along three parallel lines. The flow parameters in the boundary layer and separated regions adjacent to the model surface were measured by traversing hot wire and pitot probes. The traverses were taken across the boundary layer and reversed flow regions in a direction normal to the body surface; they were made in several vertical planes, including the plane of symmetry.
    Keywords: AERODYNAMICS
    Type: AGARD Flow Separation; 13 p
    Format: text
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  • 93
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    An experimental and numerical investigation of shock wave induced turbulent boundary layer separation at hypersonic speeds (1975)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: A thoroughly documented experiment is reported that was specifically designed to test and guide computations of the interaction of an impinging shock wave with a turbulent boundary layer. Detailed mean flow field and surface data are presented for two shock strengths which resulted in attached and separated flows, respectively. Numerical computations are used to illustrate the dependence of the computations on the particulars of the turbulence models. Models appropriate for zero pressure gradient flows predicted the overall features of the flow fields, but were deficient in predicting many of the details of the interaction regions. Improvements to the turbulence model parameters were sought through a combination of detailed data analysis and computer simulations which tested the sensitivity of the solutions to model parameter changes. Computer simulations using these improvements are presented and discussed.
    Keywords: AERODYNAMICS
    Type: AGARD Flow Separation; 13 p
    Format: text
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  • 94
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    On the calculation of supersonic separating and reattaching flows (1975)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: A method is developed for solving the laminar and turbulent compressible boundary layer equations for separating and reattaching flows. Results of this method are compared with experimental data for two laminar and three turbulent layer, shock wave interactions. Several Navier-Stokes solutions are obtained for each of the laminar boundary layer, shock wave interactions considered. Comparison of these solutions indicates a first order sensitivity in C sub f to the computational mesh selected in both the viscous and inviscid portions of the flow. Comparison of the present boundary layer solutions with the Navier-Stokes solutions and with data for a given Mach number indicates that as long as the separation bubble is small, the boundary layer approximation yields solutions whose accuracy is comparable to the Navier-Stokes solutions.
    Keywords: AERODYNAMICS
    Type: AGARD Flow Separation; 12 p
    Format: text
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  • 95
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    Review of drag measurements from flight tests of manned aircraft with comparisons to wind-tunnel predictions (1973)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: In-flight studies of the overall and local components of drag of many types of aircraft were conducted. The primary goal of these studies was to evaluate wind-tunnel and semiempirical prediction methods. Some evaluations are presented in this paper which may be summarized by the following observations: Wind-tunnel predictions of overall vehicle drag can be accurately extrapolated to flight Reynolds numbers, provided that the base drag is removed and the boattail areas on the vehicle are small. The addition of ablated roughness to lifting body configurations causes larger losses in performance and stability than would be expected from the added friction drag due to the roughness. Successful measurements of skin friction have been made in flight to Mach numbers above 4. A reliable inflatable deceleration device was demonstrated in flight which effectively stabilizes and decelerates a lifting aircraft at supersonic speeds.
    Keywords: AERODYNAMICS
    Type: AGARD Aerodyn. Drag; 12 p
    Format: text
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  • 96
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    A summary of current research in rotor unsteady aerodynamics with emphasis on work at Langley Research Center (1973)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: The basic unsteady aerodynamic environment of the rotary wing is summarized. Some of the observed trends in the state of the art are discussed. Some of the research needs that will require attention are reported. A review of a number of research investigations as a part of a joint NASA/Army rotorcraft project is presented. The research is directed toward achieving a better understanding of rotor unsteady airfoils. The investigations include: (1) rotor maneuver loads; (2) level flight and maneuver wake prediction; (3) tip-vortex flow; (4) blade-vortex interactions; (5) dynamic stall; (6) transient Mach number air loads; and (7) development of variable geometry rotors.
    Keywords: AERODYNAMICS
    Type: AGARD Aerodyn. of Rotary Wings; 20 p
    Format: text
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  • 97
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    Injection into a supersonic stream from the windward side of sweptback injectors at angle of attack (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Windward injection into supersonic stream at angle of attack, minimizing vortex disruption
    Keywords: AERODYNAMICS
    Type: ; 394-398. (
    Format: text
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  • 98
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    Viscous slipstream flow downstream of a centerline Mach reflection (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Viscous slipstream flow downstream of triple shock wave intersection in supersonic diffuser air flow, using Pitot and static pressure probe measurements
    Keywords: AERODYNAMICS
    Type: ; - ASTRONOMY 1969- TE
    Format: text
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  • 99
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    Semiempirical calculations of the interaction of a slightly underexpanded jet with a quiescent atmosphere (1970)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Retrorocket jet size and structure for scientific instruments soft Mars landing, estimating off- optimum supersonic jet interaction with quiescent atmosphere
    Keywords: AERODYNAMICS
    Type: ; STITUTION OF ENGINEE
    Format: text
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  • 100
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    Some simple scaling relations for heating of ballistic entry bodies (1970)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Scaling relations showing effects of ballistic coefficient, flight path angle and inverse atmospheric scale height on heating of ballistic entry bodies
    Keywords: AERODYNAMICS
    Type: ; STITUTION OF ENGINEE
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