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  • AERODYNAMICS  (928)
  • 1980-1984  (708)
  • 1970-1974  (220)
  • 1981  (366)
  • 1980  (342)
  • 1970  (220)
Collection
Keywords
Years
  • 1980-1984  (708)
  • 1970-1974  (220)
Year
  • 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
    Publication Date: 2011-10-14
    Description: 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.
    Keywords: AERODYNAMICS
    Type: AGARD Dyn. Stability Parameters; 13 p
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  • 2
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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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  • 3
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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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  • 4
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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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  • 5
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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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  • 6
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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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  • 7
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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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  • 8
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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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  • 9
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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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  • 10
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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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  • 11
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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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  • 12
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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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  • 13
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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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  • 14
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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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  • 15
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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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  • 16
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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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  • 17
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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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  • 18
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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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  • 19
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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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  • 20
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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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  • 21
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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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  • 22
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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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  • 23
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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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  • 24
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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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  • 25
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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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  • 26
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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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  • 27
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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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  • 28
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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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  • 29
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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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  • 30
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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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  • 31
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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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  • 32
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    An analytic solution to the classical two-body problem with drag (1981)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The two body problem was analyzed with a specific drag model. The model treats drag as a force proportional to the vector velocity and inversely proportional to the distance to the center of attraction. The solution is expressed in terms of known functions and is of a simple and compact form. The time of flight is expressed as a quadrature in the true anomaly. The results are: (1) development of a vector differential equation which allows analysis of an infinite number of gravitational and drag models; and (2) obtaining the solution of a linear differential equation using the inverse method of laplace transforms.
    Keywords: AERODYNAMICS
    Type: Houston Univ. The 1981 NASA ASEE Summer Fac. Fellowship Program, Vol. 2; 22 p
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  • 33
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    Langley high-lift research on a high-aspect-ratio supercritical wing configuration (1981)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: To determine the low speed performance characteristics of a representative high aspect ratio supercritical wing, two low speed jet transport models were fabricated. A 12-ft. span model was used for low Reynolds number tests in the Langley 4- by 7-Meter Tunnel and the second, a 7.5-ft. span model, was used for high Reynolds number tests in the Ames 12-foot Pressure Tunnel. A brief summary of the results of the tests of these two models is presented and comparisons are made between the data obtained on these two models and other similar models. Follow-on two and three dimensional research efforts related to the EET high-lift configurations are also presented and discussed.
    Keywords: AERODYNAMICS
    Type: Advan. Aerodyn.: Selected NASA Res.; p 55-77
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  • 34
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    Measured transonic unsteady pressures on an energy efficient transport wing with oscillating control surfaces (1981)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Highlight results are presented from subsonic and transonic pressure measurement studies conducted in the Langley Transonic Dynamics Tunnel on a supercritical wing model representative of an energy efficient transport design. Steady- and unsteady-pressure data were acquired on the upper and lower wing surface at an off-design Mach number of 0.60 and at the design Mach number of 0.78, for a Reynolds number of 2.2 x 10(6) (based on the wing average chord). The model configuration consisted of a sidewall-Mounted half-body fuselage and a semi-span wing with an aspect ratio of 10.76, a leading-edge sweepback angle of 28.8 degrees, and supercritical airfoil sections. The wing is instrumented with 252 static pressure orifices and 164 dynamic pressure gages. Model test variables included wing angle of attack, control-surface mean deflection angle, control-surface oscillating deflection angle and frequency, and phasing between oscillating leading-edge and trailing-edge controls when used together.
    Keywords: AERODYNAMICS
    Type: Advan. Aerodyn.: Selected NASA Res.; p 21-36
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  • 35
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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
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  • 36
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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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  • 37
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    Results from a new wind-tunnel apparatus for studying coning and spinning motions of bodies of revolution (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Wind tunnel apparatus for reproducing coning and spinning motions of bodies of revolution, using six-component strain gage balance for aerodynamic forces
    Keywords: AERODYNAMICS
    Type: ; UGREVUE(
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  • 38
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    Blunt slender cones in viscous hypersonic flow (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Heat transfer and shock wave shapes about blunt slender cones in viscous-inviscid coupling hypersonic flow
    Keywords: AERODYNAMICS
    Type: ; UGREVUE(
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  • 39
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    Changes in heat transfer from turbulent boundary layers interacting with shock waves and expansion waves (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Heat transfer from turbulent boundary layer interacting with shock and expansion waves in supersonic flow
    Keywords: AERODYNAMICS
    Type: ; UGREVUE(
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  • 40
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    Sphere drag in near-free-molecule hypersonic flow (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Spheres drag coefficient at hypersonic Mach numbers for near free molecular flow
    Keywords: AERODYNAMICS
    Type: ; UGREVUE(
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  • 41
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    The two-dimensional oscillating airfoil in a wind tunnel in subsonic flow (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Forces on two dimensional oscillating airfoil in subsonic compressible wind tunnel flow, solving partial differential equation for pressure potential by integral transform technique
    Keywords: AERODYNAMICS
    Type: ; YAL SOCIETY (
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  • 42
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    Shock interference heating and the space shuttle (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Schlieren photographs of shock interference heating for space shuttles
    Keywords: AERODYNAMICS
    Type: NASA, WASHINGTON SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 1 JUL. 1970; P 338-389
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  • 43
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    Boundary layer transition on lifting entry vehicle configurations at high angle-of-attack (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Boundary layer transition on lifting reentry vehicles at high angles of attack
    Keywords: AERODYNAMICS
    Type: NASA, WASHINGTON SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 1 JUL. 1970; P 445-462
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  • 44
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    Static aerodynamics, flow fields and aerodynamic heating of space shuttle orbiters (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Wind tunnel tests of aerodynamic stability, boundary layer transition, and heat transfer in space shuttle orbiters
    Keywords: AERODYNAMICS
    Type: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 1 JUL. 1970; P 142-193
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  • 45
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    Measurements of local skin friction downstream of grit-type boundary-layer-transition trips at M equals 2.17 and zero heat transfer (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Supersonic skin friction measurements in grit type boundary layer transition trips with zero heat transfer
    Keywords: AERODYNAMICS
    Type: ; SEARCH(
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  • 46
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    Effect of radiation on hypersonic stagnation flow at low density (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Radiation effects on viscous hypersonic low density stagnation flow using two layer model, calculating flow field and heat transfer coefficient
    Keywords: AERODYNAMICS
    Type: ; ACE(
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  • 47
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    Vehicle flight scaling with aerodynamic flow hysteresis (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Missile oscillations in plane during pitching moment hysteresis, discussing test coefficients suitability for predicting motion
    Keywords: AERODYNAMICS
    Type: ; RO(
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  • 48
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    Effect of vortices on delta wing lee-side heating at Mach 6 (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Off-centerline heating on lee surface of supersonic delta wing with separation and vortex initiation at leading edge
    Keywords: AERODYNAMICS
    Type: ; ADEMIE DES SCIENCES
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  • 49
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    Viscous effects on the flow coefficient for a supersonic nozzle (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Adiabatic flow coefficient in supersonic nozzle with choked flow conducted over throat Reynolds number range
    Keywords: AERODYNAMICS
    Type: ; ADEMIE DES SCIENCES
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  • 50
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    Computation of ionization in re-entry flowfields (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Electron concentration profiles in blunt nose vehicle shock layer during atmospheric near orbital entry at high altitudes, using finite rate chemistry
    Keywords: AERODYNAMICS
    Type: ; ADEMIE DES SCIENCES
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  • 51
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    Vortex-flow aerodynamics - An emerging design capability (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Promising current theoretical and simulational developments in the field of leading edge vortex-generating delta, arrow ogival wings are reported, along with the history of theory and experiment leading to them. The effects of wing slenderness, leading edge nose radius, Mach number and incidence variations, and planform on the onset of vortex generation and redistribution of aerodynamic loads are considered. The range of design possibilities in this field are consequential for the future development of strategic aircraft, supersonic transports and commercial cargo aircraft which will possess low-speed, high-lift capability by virtue of leading edge vortex generation and control without recourse to heavy and expensive leading edge high-lift devices and compound airfoils. Attention is given to interactive graphics simulation devices recently developed.
    Keywords: AERODYNAMICS
    Type: Astronautics and Aeronautics; 19; May 1981
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  • 52
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    Longitudinal grooves for bluff body drag reduction (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Wind tunnel test results are presented for four axisymmetric bluff body configurations in order to determine their effect on form and pressure drag. It was found that drag reductions on the order of 40% are obtainable with an afterbody incorporating four longitudinal 'V' grooves. Although this effect may be due to the functioning of the grooves as longitudinal, continuous vortex generators, it is concluded that further research is needed to elucidate the physical basis of the test results. Optimization of the effect will be useful in base drag reduction for such vehicles as automobiles and cargo aircraft with sharply upswept afterbodies.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Apr. 198
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  • 53
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    Vectored injection into compressible laminar and turbulent boundary layers (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A fundamental analysis of two-dimensional supersonic boundary layer flow, both laminar and turbulent, is presented for a wide range of normal and nonnormal mass-transfer velocities. The analysis is based on the numerical solution of the Navier-Stokes equations, and results are compared with available theoretical and experimental data. Certain cases of practical importance, for which results are not presently available, are referred to.
    Keywords: AERODYNAMICS
    Type: Computer Methods in Applied Mechanics and Engineering; 25; Jan. 198
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  • 54
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    Three-layer interactive method for computing supersonic laminar separated flows (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: An interactive model for numerical computation of complicated two-dimensional flowfields including regions of reversed flow is proposed. The present approach is one of dividing the flowfield into three regions, in each of which a simplified mathematical model is applied: (1) outer, supersonic flow for which the full potential equation (hyperbolic) is used; (2) viscous, laminar layer in which the compressible boundary-layer model (parabolic) is used; and (3) recirculating flow modeled by the incompressible Navier-Stokes equations (elliptic). For matching of the numerical solutions in the three layers, two interaction models are developed: one for pressure interaction, the other for interaction between the shear layer and the recirculating flow. The uniform solution for the whole flowfield is then obtained by iteration of the local solutions under the constraints imposed by matching. The three-layer interactive model is used for solution of the flowfield past an asymmetric cavity. The method is shown to be capable of dealing with backflow without encountering problems at separation, characteristic to the boundary-layer approach.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 18; Nov. 198
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  • 55
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    Report of the panel on theoretical aerodynamics (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Interactions between theoretical aerodynamics and the NTF are discussed. The development and validation of computational fluid dynamics computer codes, the determination of Reynolds number scaling laws, and extension of the data bases of entrainment type turbulence models to include high Reynolds number data are recommended areas of study. The major benefit theoretical aerodynamics could have on the NTF is in the quantitative description of wind tunnel wall interference effects.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 277-286
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  • 56
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    High Reynolds number research requirements for space vehicle design (1981)
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    Publication Date: 2011-08-18
    Description: Requirements of entry vehicle design requiring high Reynolds number wind tunnel testing are discussed. The space shuttle orbiter, development of future space transportation systems, and planetary entry data analysis are considered.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 265-274
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  • 57
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    Report of the panel on aeroelasticity and unsteady aerodynamics (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The status of recommended areas of study for the NTF are reviewed. Transonic and control surface unsteady aerodynamics, and buffet onset and loads are considered. Testing of dynamically scaled flutter models is discussed.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 237-246
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  • 58
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    Model experience in the Langley 0.3-m transonic cryogenic tunnel (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The model building, development, and testing experience gained during 8 years of operation of the 0.3-m Transonic Cryogenic Tunnel (TCT) is summarized. The summary is divided into four portions: (1) models tested in the 0.3-m TCT's original octagonal test section; (2) models tested in the present two dimensional test section; (3) models tested as a part of tunnel calibration and the development of advanced technology airfoils; and (4) development of a new way to construct two dimensional airfoil models. Design requirements imposed on the models by high Reynolds number testing at cryogenic temperatures are reviewed.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 53-73
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  • 59
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    Noise radiation from the side edges of flaps (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The recently observed phenomenon of high noise radiation from the side edges of flaps in flow is investigated by way of a simple two-dimensional model problem. The model is based upon a physical picture of boundary layer vorticity being swept around the edge by spanwise flow on the flap. The model problem is developed and solved and the resulting noise radiation calculated. Further, a mathematical condition for the vortex to be captured by the potential flow and swept around the edge is derived. The results show that the sound generation depends strongly upon the strength of the vorticity and distance from the edge and that it can be more intense than the more common trailing edge noise source in agreement with the experimental observations.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 18; May 1980
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  • 60
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    Stability aspects of diverging subsonic flow (1980)
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    Publication Date: 2011-08-17
    Description: The paper describes the computation of two-dimensional, subsonic, diverging internal flows and how they differ from the corresponding converging flows. Such diverging or decelerating flows occur in such obvious places as subsonic diffusers and inlets; however, such flows also occur in supersonic nozzles in the presence of a normal shock. The flow instability and its relation to the numerical method used, boundary conditions, and viscous effects are assessed both analytically and numerically. The inviscid flow is shown to be physically unstable and a poor representation of the true viscous flow.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 18; May 1980
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  • 61
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    Effectiveness of leading-edge vortex flaps on 60 and 75 degree delta wings (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A series of wind tunnel tests were run on 60 and 75 deg sweep delta wings to examine the effectiveness of leading-edge vortex flaps. Tests results showed that leading-edge vortex flaps are effective in giving large increases in lift-to-drag ratio and decreases in drag over a wide range of angle of attack. Tests on inverted flaps on the 60 deg delta wing showed substantial increases in lift and drag and may indicate a possibility of using inverted flaps on delta wings in the landing portion of flight. The 60 deg data were compared with that for a 75 deg sweep delta wing confirming that leading-edge vortex flap effectiveness is stronger as sweep is increased. Pitching moment effects due to vortex flaps use were also examined.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 18; Apr. 198
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  • 62
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    Partially confined multiple jet mixing (1981)
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    Publication Date: 2011-08-18
    Description: Results of hot-wire measurements in an incompressible partially confined jet issuing from an array of rectangular nozzles, equally spaced with their small dimensions aligned are presented. The quantities measured include mean velocity and the Reynolds stress in the two central planes of the jet at stations covering up to 115 widths (small dimension of a nozzle) downstream of the nozzle exit. For downstream distances greater than 60 widths, the flowfield is observed to be nearly homogenous and the turbulence appears to be quite similar to that of a grid generated turbulence.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Mar. 198
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  • 63
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    Unsteady Newton-Busemann flow theory. I - Airfoils (1981)
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    Publication Date: 2011-08-18
    Description: Newtonian flow theory for unsteady flow at very high Mach numbers is completed by the addition of a centrifugal force correction to the impact pressures. The correction term is the unsteady counterpart of Busemann's centrifugal force correction to impact pressures in steady flow. For airfoils of arbitary shape, exact formulas for the unsteady pressure and stiffness and damping-in-pitch derivatives are obtained in closed form, which require only numerical quadratures of terms involving the airfoil shape. They are applicable to airfoils of arbitrary thickness having sharp or blunt leading edges. For wedges and thin airfoils these formulas are greatly simplified, and it is proved that the pitching motions of thin airfoils of convex shape and of wedges of arbitrary thickness are always dynamically stable according to Newton-Busemann theory. Leading-edge bluntness is shown to have a favorable effect on the dynamic stability; on the other hand, airfoils of concave shape tend toward dynamic instability over a range of axis positions if the surface curvature exceeds a certain limit. As a byproduct, it is also shown that a pressure formula recently given by Barron and Mandl for unsteady Newtonian flow over a pitching power-law shaped airfoil is erroneous and that their conclusion regarding the effect of pivot position on the dynamic stability is misleading.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Mar. 198
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  • 64
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    Evidence of imbedded vortices in a three-dimensional shear flow (1981)
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    Publication Date: 2011-08-18
    Description: Vortex phenomena encountered in an investigation of the streamwise development of the three-dimensional wake region behind the tip of a three-dimensional wedge model are reported. Pressure profiles were measured by pitot probes downstream of a tip with a nearly constant surface pressure level and a nearly continuous surface curvature in a blowdown air tunnel operating at Mach 6. Rather than the simple three-dimensional quasi-parallel shear flow expected, the measurements indicated the presence of a flow with large deficits in longitudinal pitot pressure, which are usually associated with the core region of quasi-steady longitudinal vortices. Vapor screen flow visualizations also support the presence of longitudinal vortices located primarily in the tip region and evidently forming in the vicinity of the wake neck. An increase in overall wake thickness by 100% is also observed. The origin of the vortices as quasi-steady Taylor-Gortler vortices generated in the concavely curved shear layer near the wake neck is considered. It is pointed out that the existence of longitudinal vortexes suggests that three-dimensional turbulence modeling may be much more difficult than previously supposed.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Mar. 198
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  • 65
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    Proposed aeroelastic and flutter tests for the National Transonic Facility (1981)
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    Publication Date: 2011-08-18
    Description: Tests that can exploit the capability of the NTF and the transonic cryogenic tunnel, or lead to improvements that could enhance testing in the NTF are discussed. Shock induced oscillation, supersonic single degree control surface flutter, and transonic flutter speed as a function of the Reynolds number are considered. Honeycombs versus screens to smooth the tunnel flow and a rapid tunnel dynamic pressure reducer are recommended to improve tunnel performance.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center High Reynolds Number Res. - 1980; p 153-161
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  • 66
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    Report of the wind tunnel/flight correlation panel (1981)
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    Publication Date: 2011-08-18
    Description: Basic calibration of the tunnel prior to conducting any tests, the areas requiring wind tunnel/flight test correlation for validating the NTF, and recommendations for achieving validation of the NTF are discussed.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center High Reynolds Number Res. - 1980; p 249-262
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  • 67
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    High lift technology (1981)
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    Publication Date: 2011-08-18
    Description: The NASA Langley high lift technology program is reviewed and elements of the program which are considered Reynolds number sensitive are discussed. The Energy Efficient Transport (EET) and Supersonic Cruise Research (SCR) models proposed for high lift studies in the National Transonic Facility (NTF) are described. Recommendations regarding the NTF facility and test techniques are presented.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 197-213
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  • 68
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    Wall interference effects: Status review (1981)
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    Publication Date: 2011-08-18
    Description: The interference technology incorporated into the NTF design (hardware) and the emerging transonic wall interference assessment correction procedures (software) to be employed when the NTF becomes operational was reviewed. It is anticipated that the early experiments will provide data relevant to wall interference effects.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 123-241
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  • 69
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    Configuration aerodynamics (1981)
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    Publication Date: 2011-08-18
    Description: Static aerodynamic research related to aircraft configurations in their cruise or combat modes is discussed. Subsonic transport aircraft, transonic tactical aircraft, and slender wing aircraft are considered. The status and plans of Langley's NTF configuration research program are reviewed. Recommendations for near term configuration research are made.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 217-234
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  • 70
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    Comments on Reynolds number effects and the role of NTF in the development of air vehicles (1981)
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    Publication Date: 2011-08-18
    Description: The National Transonic Facility (NTF) capability to match the full scale Reynolds numbers of all but the largest airplanes is discussed. Conversion factors to enable calculation of Sl-unit equivalents for all U.S. units are listed. Using data from several facilities, analytic methods, and flight test data, a competetive aircraft in the relatively low Reynolds number was developed. The NTF offers the capability to obtain data at full scale Reynolds numbers in the cruise condition for most of the products, and will be much closer than previous tunnels to full scale Reynolds number for the operating envelopes. It is primarily on the operating envelope that Reynolds number effects are most important and least predictable.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center High Reynolds Number Res. - 1980; p 143-148
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  • 71
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    Computational aerodynamics on large computers (1980)
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    Publication Date: 2011-08-17
    Description: Three examples of advances in computational aerodynamics; (1) three-dimensional inviscid transonic analysis, (2) design calculations for wings, and (3) the computation of viscous-induced aileron buzz, are reviewed. Attention is given to wing surface pressures, design optimization, computer memory, speed and advanced solution methods on parallel computer architecture. It is determined that many implicit approximate-factorization schemes, that have been developed for Navier-Stokes equations, can be coded to run efficiently on microprocessors.
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  • 72
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    Wing flapping with minimum energy (1980)
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    Publication Date: 2011-08-18
    Description: A technique employed by Prandtl and Munk is adapted for the case of a wing in flapping motion to determine its lift distribution. The problem may be reduced to one of minimizing induced drag for a specified and periodically varying bending moment at the wing root. It is concluded that two wings in close tandem arrangement, moving in opposite phase, would eliminate the induced aerodynamic losses calculated
    Keywords: AERODYNAMICS
    Type: Aeronautical Journal; 84; July 198
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  • 73
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    The effect of finite turbulence spatial scale on the amplification of turbulence by a contracting stream (1980)
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    Publication Date: 2011-08-17
    Description: The turbulence downstream of a rapid contraction is calculated for the case when the turbulence scale can have the same magnitude as the mean-flow spatial scale. The approach used is based on the formulation of Goldstein (1978) for turbulence downstream of a contraction, with the added assumptions of a parallel mean flow at downstream infinity and turbulence calculated far enough downstream so that the nonuniformity of the mean flow field has decayed, and by treating the inverse contraction ratio as a small parameter. Consideration is given to the large-contraction-ratio and classical rapid-distortion theory limits, and to results at an arbitrary contraction ratio. It is shown that the amplification effect of the contraction is reduced when the spatial scale of the turbulence increases, with the upstream turbulence actually suppressed for a contraction ratio less than five and a turbulence spatial scale greater than three times the transverse dimensions of the downstream channel.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 98; June 12
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  • 74
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    Types of leeside flow over delta wings (1980)
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    Publication Date: 2011-08-17
    Description: It is noted that so far most systematic investigations on the lee side flow over delta wings at supersonic speeds are concerned with flat upper surfaces. On the basis of these results, the paper makes an attempt to characterize the different types of flow over a wing with a delta-shaped upper surface by varying a number of parameters. It is concluded that the work should be considered a first step toward systematizing the flow over delta-shaped lee sides as well.
    Keywords: AERODYNAMICS
    Type: Zeitschrift fuer Flugwissenschaften und Weltraumforschung; 4; Mar
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  • 75
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    Solution of the transonic full potential equation in conservative form using an implicit algorithm (1981)
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    Publication Date: 2011-08-18
    Description: The paper presents numerical solutions of the full potential equation in conservative form. The iteration scheme used is a fully implicit approximate factorization technique and provides a significant improvement in convergence speed relative to standard successive line overrelaxation algorithms. The spatial differencing algorithm is centrally differenced in both subsonic and supersonic regions to maintain stability. This effectively approximates rotated differencing, thereby greatly improving the reliability of the algorithm.
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  • 76
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    Computation of airfoil buffet boundaries (1981)
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    Publication Date: 2011-08-18
    Description: The ILLIAC IV computer has been programmed with an implicit, finite-difference code for solving the thin layer compressible Navier-Stokes equation. Results presented for the case of the buffet boundaries of a conventional and a supercritical airfoil section at high Reynolds numbers are found to be in agreement with experimentally determined buffet boundaries, especially at the higher freestream Mach numbers and lower lift coefficients where the onset of unsteady flows is associated with shock wave-induced boundary layer separation.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Nov. 198
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  • 77
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    Application of unsteady airfoil theory to rotary wings (1981)
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    Publication Date: 2011-08-18
    Description: A clarification is presented on recent work concerning the application of unsteady airfoil theory to rotary wings. The application of this theory may be seen as consisting of four steps: (1) the selection of an appropriate unsteady airfoil theory; (2) the resolution of that velocity which is the resultant of aerodynamic and dynamic velocities at a point on the elastic axis into radial, tangential and perpendicular components, and the angular velocity of a blade section about the deformed axis; (3) the expression of lift and pitching moments in terms of the three components; and (4) the derivation of explicit expressions for the components in terms of flight velocity, induced flow, rotor rotational speed, blade motion variables, etc.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 18; July 198
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  • 78
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    Starting criterion for hypersonic inlets (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Starting criterion for hypersonic inlets with large turbulent boundary layers, considering total pressure recovery from all shock and viscous losses
    Keywords: AERODYNAMICS
    Type: ; YSICA STATUS SOLIDI
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  • 79
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    Generalized one-dimensional, compound compressible nozzle flow (1970)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: One dimensional compound compressible nozzle flow solution dependence on initial conditions and nozzle geometry, discussing applications to bypass turbojets and solid propellant motors
    Keywords: AERODYNAMICS
    Type: ; ADEMIE DES SCIENCES
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  • 80
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    Wind-vehicle interaction in flight - Methods of analysis (1970)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: Wind effects on launch vehicle and equations of motion of vehicle
    Keywords: AERODYNAMICS
    Type: AGARD WIND EFFECTS ON LAUNCH VEHICLES FEB. 1970; P 199-226
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  • 81
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    Aerodynamic considerations (1970)
    In:  CASI
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    Publication Date: 2012-05-22
    Description: Aerodynamic loads produced by winds and launch vehicle designing
    Keywords: AERODYNAMICS
    Type: AGARD WIND EFFECTS ON LAUNCH VEHICLES FEB. 1970; P 75-114
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  • 82
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    The coupling between flow instabilities and incident disturbances at a leading edge (1981)
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    Publication Date: 2011-08-18
    Description: It is now generally agreed that an external disturbance field, such as an incident acoustic wave, can effectively couple to instabilities of a flow past a trailing edge. One purpose of the present paper is to show that there are situations where a similar coupling can occur at a leading edge. The process is analyzed and the effects of experimentally controllable parameters are assessed. It is important to account for such phenomena when evaluating the effect of external disturbances on transition.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 104; Mar. 198
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  • 83
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    A discrete vortex method for the non-steady separated flow over an airfoil (1981)
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    Publication Date: 2011-08-18
    Description: A discrete vortex method was used to analyze the separated non-steady flow about a cambered airfoil. The foil flow modelling is based on the thin lifting-surface approach, where the chordwise location of the separation point is assumed to be known from experiments or flow-visualization data. Calculated results provided good agreement when compared with the post-stall aerodynamic data of two airfoils. Those airfoil sections differed in the extent of travel of the separation point with increasing angle of attack. Furthermore, the periodic wake shedding was analyzed and its time-dependent influence on the airfoil was investigated.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 102; Jan. 198
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  • 84
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    Thin-layer approximation for three-dimensional supersonic corner flows (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The thin-layer approximation is extended to an axial corner that is formed by the intersection of two perpendicular plates, one of which has an inclination angle with respect to the free stream. A computer code developed by Hung and MacCormack (1978) is modified for the thin-layer approximation, and a case with Mach 5.9 and a wedge angle of 6 deg is computed. In addition, it is shown that it is not necessary to solve the complete Navier-Stokes equations for a three-dimensional high-Reynolds-number corner flow.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 18; Dec. 198
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  • 85
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    Pathfinder model program for the National Transonic Facility (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: An overview of the Pathfinder Models Program is presented. The Pathfinder program is a major research and development activity in support of the National Transonic Facility Activation Plan. The program scope, models design approach, and Pathfinder model configurations are presented along with a discussion of major supportive program activities. The anticipated design criteria for NTF models are presented.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 37-52
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  • 86
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    Flowfield calculations past an entry probe with ablated nose shape (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The effects of ablated nose shapes on the flowfield solutions are studied, using a time-dependent finite-difference method developed by Kumar, et al. (1979). Solutions are obtained for the laminar flow of a radiating mixture of H-He in chemical equilibrium past a blunt axisymmetric body at zero angle of attack. The freestream conditions correspond to a point on a typical Jovian entry trajectory, and the initial probe shape is a 45-deg half-angle spherically blunted cone. It is found that as nose bluntness increases, the following occur: in the nose region, shock standoff distances and radiative heating rates increase substantially; surface pressure level increases, but convective heating rates decrease.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 18; June 198
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  • 87
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    Unified treatment of lifting atmospheric entry (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: This paper presents a unified treatment of the effect of lift on peak acceleration during atmospheric entry. Earlier studies were restricted to different regimes because of approximations invoked to solve the same transcendental equation. This paper shows the connection between the earlier studies by employing a general expression for the peak acceleration and obtains solutions to the transcendental equation without invoking the earlier approximations. Results are presented and compared with earlier studies where appropriate.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 17; Mar
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  • 88
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    Trailing edge noise prediction using Amiet's method (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Amiet's (1976, 1978) solution to the problem of airfoil trailing edge noise prediction is discussed in light of the results of evanescent wave theory's application to the measured surface pressure behavior near the trailing edge of an airfoil with a turbulent boundary layer. The method employed by Amiet has the advantage of incorporating the effect of finite chord in its solution. The assumed form of the pressure distribution is examined as well as the constant turbulent boundary layer convection assumption, which is found to be unnecessarily restrictive.
    Keywords: AERODYNAMICS
    Type: Journal of Sound and Vibration; 77; Aug. 8
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  • 89
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    Forebody drag reduction (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: It is shown that the mechanisms of forebody drag reduction by means of either a spike or a forward-facing jet are similar, with the maximum achievable drag reduction being of the same order. Because the jet may be a relatively cool gas, however, the forward facing jet has the additional capability of reducing the aerodynamic heating that is so severe at high Mach numbers. By means of the correlation presented, jet ejection parameters may be chosen to achieve maximum permissible forebody drag reduction. The correlation method uses a momentum coefficient that characterizes jet efflux and freestream conditions.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Oct. 198
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  • 90
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    Unsteady Newton-Busemann flow theory. II - Bodies of revolution (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A complete Newtonian flow theory is presented for unsteady flow past oscillating bodies of revolution of general shape at very high Mach numbers, consideration being given to a centrifugal force correction to the impact pressures. Expressions are obtained for the unsteady pressure and the stability derivatives are presented in closed form. It is stressed that the correction for the centrifugal force, which arises because of the curved trajectories that fluid particles follow along the surface subsequent to their impact, must not be neglected. If the correction is included, the theory is shown to be in excellent agreement with experimental results for relatively sharp cones. Theoretical results are in poor agreement with experimental results in air for bodies having moderate or large-nose bluntness.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Oct. 198
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  • 91
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    Top-mounted inlet system feasibility for transonic-subsonic fighter aircraft applications (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: To inlet flow field and engine inlet performance data for an advanced fighter aircraft configuration were obtained over the Mach 0.6 to 2.0 range. The studies not only provided extensive data for the baseline arrangement, but also evaluated the effects of key aircraft configuration variables (inlet location, canopy-dorsal integration, wing leading-edge extension planform area, and variable incidence canards) on top inlet performance. In order to set these data in the context of practical aircraft systems top inlet performance is compared with that of more conventional inlet/airframe integrations. The results of these evaluations show that, for the top inlet configuration tested, relatively good inlet performance and compatibility characteristics are maintained during subsonic and transonic maneuver. However, at supersonic speeds, flow expansion over the forebody and wings causes an increase in local inlet Mach number subsequently reduces inlet performance levels. These characteristics infer that although top inlets many not pose a viable design option for aircraft requiring a high degree of supersonic maneuverability, they have distinct promise for vehicles with subsonic and transonic maneuver capabilities.
    Keywords: AERODYNAMICS
    Type: AGARD Aerodyn. of Power Plant Installation; 17 p
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  • 92
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    Impact of high-alpha aerodynamics on dynamic stability parameters of aircraft and missiles (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The aerodynamic phenomena associated with high angles of attack and their effects on the dynamic stability characteristics of airplane and missile configurations are examined. Information on dynamic effects is limited. Steady flow phenomena and their effects on the forces and moments are reviewed. The effects of asymmetric vortices and of vortex bursting on the dynamic response of flight vehicles are reviewed with respect to their influence on: (1) nonlinearity of aerodynamic coefficients with attitude, rates, and accelerations; (2) cross coupling between longitudinal and lateral directional models of motion; (3) time dependence and hysteresis effects; (4) configuration dependencey; and (5) mathematical modeling of the aerodynamics.
    Keywords: AERODYNAMICS
    Type: AGARD Dyn. Stability Parameters; 18 p
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  • 93
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    An assessment of theoretical models for viscous and transonic flow (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Topics discussed include shear flow models, simplified models for treating separation, classical linear theory, a local linearization theory, a transonic linear theory, a transonic nonlinear theory, the experiment of Davis, and the experiment of Tijdeman. It is concluded that shear flow models, which have proven very accurate in taking into account boundary layer effects for panel flutter, are likely to be less so for lifting surface flutter. For many applications in transonic flow, transonic linear theory will be adequate.
    Keywords: AERODYNAMICS
    Type: AGARD Boundary Layer Effects on Unsteady Airloads; 28 p
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  • 94
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    Experimental studies of scale effects on oscillating airfoils at transonic speeds (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Scale effects are discussed with reference to a conventional airfoil (NACA 64A010) and a supercritical airfoil (NLR 7301) at mean flow conditions that support both weak and strong shock waves. During the experiment the Reynolds number was varied from 3 x 10 to the sixth power at time history data are presented over the range of reduced frequencies that are important in aeroelastic applications. The experimental data show that viscous effects are important in the case of the supercritical airfoil at all flow conditions and in the case of the conventional airfoil under strong shock wave conditions. Some frequency dependent viscous effects were also observed.
    Keywords: AERODYNAMICS
    Type: AGARD Boundary Layer Effects on Unsteady Airfoils; 13 p
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  • 95
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    Theoretical and Experimental studies of aerodynamic interference effects (1980)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Theoretical studies of aerodynamic forces on winglets shed considerable light on the mechanism by which these devices can reduce drag at constant total lift and on the necessity for proper alignment and cambering to achieve optimum favorable interference. Results of engineering studies, wind tunnel tests and performance predictions are reviewed for installations proposed for the AMST YC-14 and the KC-135 airplanes. The other major area of aerodynamic interference discussed is that of engine nacelle installations. Slipper and overwing nacelles have received much attention because of their potential for noise reduction, propulsive lift and improved ground clearance. A major challenge is the integration of such nacelles with the supercritical flow on the upper surface of a swept wing in cruise at high subsonic speeds.
    Keywords: AERODYNAMICS
    Type: AGARD Subsonic(Transonic Configuration Aerodyn.; 19 p
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  • 96
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    Numerical solution techniques for unsteady transonic aerodynamics problems (1980)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Basic concepts of finite difference solution techniques for unsteady transonic flows are presented. The hierarchy of mathematical forumulations that approximate the Navier-Stokes equations are reviewed. The basic concepts involved in constructing numerical algorthms to solve these formulations are given. Semi-implicit and implicit schemes are constructed and analyzed. The discussion focuses primarily on techniques for solving the low frequency transonic small disturbance equation. This is the simplest formulation that contains the essence of inviscid unsteady transonic flow physics. The low frequency formulation is emphasized here because codes based on this theory can be run in minutes of processor time on currently available computers. Furthermore, numerical techniques involved in solving this simple formulation also apply to the more complicated formulations. Extensions to these formulations are briefly described. An indication of the present capability for solving unsteady transonic flows is provided. Important areas of future research for the advancement of computational unsteady transonic aerodynamics are described.
    Keywords: AERODYNAMICS
    Type: AGARD Spec. Course on Unsteady Aerodyn.; 24 p
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  • 97
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    Use of advanced computers for aerodynamic flow simulation (1980)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The current and projected use of advanced computers for large-scale aerodynamic flow simulation applied to engineering design and research is discussed. The design use of mature codes run on conventional, serial computers is compared with the fluid research use of new codes run on parallel and vector computers. The role of flow simulations in design is illustrated by the application of a three dimensional, inviscid, transonic code to the Sabreliner 60 wing redesign. Research computations that include a more complete description of the fluid physics by use of Reynolds averaged Navier-Stokes and large-eddy simulation formulations are also presented. Results of studies for a numerical aerodynamic simulation facility are used to project the feasibility of design applications employing these more advanced three dimensional viscous flow simulations.
    Keywords: AERODYNAMICS
    Type: AGARD The Use of Computers as a Design Tool; 12 p
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  • 98
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    Natural laminar flow data from full-scale flight and wind-tunnel experiments (1981)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: Experimental results obtained at NASA Langley during studies of natural laminar flow (NLF) over commercially produced aircraft surfaces are reported. The general aviation aircraft examined were light aircraft, yet displayed NLF extents close to the maximum available and equivalent to high performance business aircraft flying envelopes. Sublimating chemicals and acoustic detection techniques were employed to measure the boundary layer transition. Theoretical predictions of boundary layer stability were found to match well with the experimental data, with consideration given to both swept wings and the amplitudes of allowable waves on the airfoil surfaces. The presence of the NLF on the airfoil surfaces confirmed the benefits available from use of composite materials for airfoil surfaces.
    Keywords: AERODYNAMICS
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  • 99
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    Wind tunnel test results of a new leading edge flap design for highly swept wings, a vortex flap (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A leading edge flap design for highly swept wings, called a vortex flap, was tested on an arrow wing model in a low speed wind tunnel. A vortex flap differs from a conventional plain flap in that it has a leading edge tab which is counterdeflected from the main portion of the flap. This results in intentional separation at the flap leading edge, causing a vortex to form and lie on the flap. By trapping this vortex, the vortex flap can result in significantly improved wing flow characteristics relative to conventional flaps at moderate to high angles of attack, as demonstrated by the flow visualization results of this tests.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Supersonic Cruise Res. 1979, Pt. 1; p 131-147
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  • 100
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    Natural Laminar Flow Flight Experiment (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A supercritical airfoil section was designed with favorable pressure gradients on both the upper and lower surfaces. Wind tunnel tests were conducted in the Langley 8 Foot Transonic Pressure Tunnel. The outer wing panels of the F-111 TACT airplane were modified to incorporate partial span test gloves having the natural laminar, flow profile. Instrumentation was installed to provide surface pressure data as well as to determine transition location and boundary layer characteristics. The flight experiment encompassed 19 flights conducted with and without transition fixed at several locations for wing leading edge sweep angles which varied from 10 to 26 at Mach numbers from 0.80 to 0.85 and altitudes of 7620 meters and 9144 meters. Preliminary results indicate that a large portion of the test chord experienced laminar flow.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Advan. Aerodyn. and Active Controls; p 135-144
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