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  • Other Sources  (136)
  • AERODYNAMICS  (133)
  • Nuclear explosion
  • 1985-1989  (136)
  • 1980-1984
  • 1940-1944
  • 1985  (136)
  • 1
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    An investigation of the tabbed vortex flap (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 22; 490-497
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A new approach to the free wake problem for hovering rotors (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: In the present approach to the hovering rotor free wake problem, an influence coefficient solution method is used to find that rotor wake solution which is steady in a reference frame that rotates with the blades; this scheme solves directly for the conditions of free wake equilibrium by a procedure that does not involve time-stepping and the associated use of numerical damping or special convergence methods. The solution method has been implemented in a hover wake computer program having a three-part wake model for the tip vortex. All three wake regions are represented by the new Basic Curved Vortex Elements. Sample hover calculations are presented for single blade and multiblade rotors.
    Keywords: AERODYNAMICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    The trailing edge of a pitching airfoil at high reduced frequencies (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Trailing edge flows are visualized for a pitching airfoil. The validity of the quasi-steady and an extension to an unsteady Kutta condition are examined. A new dynamic similarity parameter is proposed.
    Keywords: AERODYNAMICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Performance and loads data from a hover test of a full-scale XV-15 rotor (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A hover test of a full-scale XV-15 rotor was conducted at the Outdoor Aerodynamic Research Facility at Ames Research Center. The primary objective of the test was to obtain accurate measurements of the hover performance of the original, metal-blade XV-15 rotor system. Data were acquired for rotor tip Mach numbers ranging from 0.60 to 0.73. This report presents data on rotor performance, rotor wake downwash velocities, and rotor loads.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86833 , REPT-85404 , NAS 1.15:86833
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Experimental and numerical investigation of supersonic flow through a square duct (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Steady, developing, adiabatic supersonic flow in a square duct is investigated for an inlet Mach number of 3.91 and a unit Reynolds number of 1.8 x 10 to the 6th/m. The numerical results for laminar flow show that two secondary flow cells develop in the near vicinity of the corner which are centered about the corner bisector and distort the primary flow in this region. For turbulent flow, the experimental results indicate that two secondary flow cells also develop about the corner bisector, but are directed in an opposite sense to that observed for the laminar case. Numerical results based on the Baldwin-Lomax model show that this model is incapable of predicting turbulence-generated secondary flow cells. For a suitable choice of constants, the Gessner-Emery model is able to predict the strength of these cells, but is deficient with respect to predicting their positions in the flow and their distorting influence on the primary flow. These observations are based on comparisons made in this paper between predicted and measured total pressure contours, cross flow velocity profiles, and local wall shear stress distributions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-1622
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Vapor-screen technique for flow visualization in the Langley Unitary Plan Wind Tunnel (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The vapor-screen technique for flow visualization, as developed for the Langley Unitary Plan Wind Tunnel, is described with evaluations of light sources and photographic equipment. Test parameters including dew point, pressure, and temperature were varied to determine optimum conditions for obtaining high-quality vapor-screen photographs. The investigation was conducted in the supersonic speed range for Mach numbers from 1.47 to 4.63 at model angles of attack up to 35 deg. Vapor-screen photographs illustrating various flow patterns are presented for several missile and aircraft configurations. Examples of vapor-screen results that have contributed to the understanding of complex flow fields and provided a basis for the development of theoretical codes are presented with reference to other research.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86384 , L-15902 , NAS 1.15:86384
    Format: application/pdf
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  • 7
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    Slender body theory and Space Shuttle transonic aerodynamics (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A computational implementation of transonic slender body theory and the equivalence rule has been utilized to study transonic flow field around the Space Shuttle Orbiter. The far field is described by a nonlinear axisymmetric Karman-Guderley model and the near field by a cross flow Laplace equation boundary value problem. The latter is treated using a source panel method. Preliminary comparisons with experiments give encouraging indications that the model can be useful for quick turnaround estimates. Areas of refinement to obtain more accurate predictions are discussed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0478
    Format: text
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  • 8
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    Effect of variable surface catalysis on heating near the stagnation point of a blunt body (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper describes arc-jet data obtained on the performance of glass coated thermal protection systems in a convectively heated environment. These data confirm earlier flight and arc-jet data that show an increased surface catalysis with salt contamination and a decreased surface catalysis near the softening point temperature of the glass. In addition, surface temperature distributions along sphere-cones with abruptly changing surface catalysis were measured near the stagnation point and compared well with computations using a reacting boundary layer code.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0248
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Euler calculations for multielement airfoils using Cartesian grids (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A finite volume formulation for the Euler equations using Cartesian grids is presented and used to study complex two-dimensional configurations. The formulation extends methods developed for the potential equation to the Euler equations. Results using this approach for single element airfoils are shown to be competitive with and as accurate as other methods that employ mapped grids. Further, it is demonstrated that this method provides a simple and accurate procedure for solving flow problems involving multielement airfoils.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0291
    Format: text
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  • 10
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    Vortex research facility improvements and preliminary density stratification effects on vortex wakes (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Recent modernization of NASA's Vortex Research Facility is described. The facility has a 300-ft test section, scheduled for a 300-ft extension, with constant test speeds of the model up to 100 ft/sec. The data acquisition hardware and software improvements included the installation of a 24-channel PCM system onboard the research vehicle, and a large dedicated 16-bit minicomputer. Flow visualization of the vortex wake in the test section is by particle seeding, and a thin sheet of argon laser light perpendicular to the line of flight; detailed flow field measurements are made with a laser velocimeter optics system. The improved experimental capabilities of the facility were used in a study of atmospheric stratification effects on wake vortex decay, showing that the effects of temperature gradient must be taken into account to avoid misleading conclusions in wake vortex research.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0050
    Format: text
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    NASA TECHNICAL REPORTS
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