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  • AERODYNAMICS  (91)
  • SOLAR PHYSICS
  • 1980-1984  (131)
  • 1975-1979
  • 1982  (131)
  • 1
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    NASA Langley laminar flow control airfoil experiment (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The design and construction of an advanced swept supercritical airfoil for commercial aircraft to be tested in a transonic wind tunnel is described. The swept LFC airfoil was designed for a given thickness ratio and lift coefficient, with emphasis placed on high critical Mach number with shock-free flow. It is compatible with satisfactory low speed and buffeting characteristics and minimizing the suction laminarization. Further emphasis was placed on achieving shock-free flow over a wide range of off-design conditions including trailing edge flap control. The requirements and design of the suction system and modifications to the Langley 8 foot transonic pressure tunnel is briefly described. Contouring of nonporous test section walls for free air simulation and flow quality improvements is included.
    Keywords: AERODYNAMICS
    Type: Laminar Flow Control; p 1-42
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Influence of surface static-pressure orifices on boundary-layer transition (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of the interaction of a laminar boundary layer and surface static-pressure orifices was conducted on a natural laminar flow airfoil. The effects of both favorable and adverse pressure gradients were studied at Reynolds numbers based on airfoil chord from approximately 500,000 to 6,000,000 with Mach number varying accordingly from about 0.03 to 0.42. The smaller the diameter of the orifice, the less likely it will cause premature transition. Locating the orifices in a chord-wise row aligned with the flow appears to have an additive, adverse effect on transition. Tube length-to-orifice diameter ration does not seem to have a consistent influence on transition.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84492 , L-15109 , NAS 1.15:84492
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Interaction of a collisionless conduction front with the chromosphere and solar hard X-ray bursts (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Keywords: SOLAR PHYSICS
    Type: Astrophysical Journal; vol. 252
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Wind-Tunnel/Flight Correlation, 1981 (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind-tunnel/flight correlation activities are reviewed to assure maximum effectiveness of the early experimental programs of the National Transonic Facility (NTF). Topics included a status report of the NTF, the role of tunnel-to-tunnel correlation, a review of past flight correlation research and the resulting data base, the correlation potential of future flight vehicles, and an assessment of the role of computational fluid dynamics.
    Keywords: AERODYNAMICS
    Type: NASA-CP-2225 , L-15368 , NAS 1.55:2225
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Experimental study of delta wing leading-edge devices for drag reduction at high lift (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The drag reduction devices selected for evaluation were the fence, slot, pylon-type vortex generator, and sharp leading-edge extension. These devices were tested on a 60 degree flatplate delta (with blunt leading edges) in the Langley Research Center 7- by 10-foot high-speed tunnel at low speed and to angles of attack of 28 degrees. Balance and static pressure measurements were taken. The results indicate that all the devices had significant drag reduction capability and improved longitudinal stability while a slight loss of lift and increased cruise drag occurred.
    Keywords: AERODYNAMICS
    Type: NASA-CR-165846
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Subsonic panel method for the efficient analysis of multiple geometry perturbations (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An accurate and efficient method was developed for the aerodynamic analysis of a series of arbitrary small geometry perturbations to a given baseline configuration. The method is appropriate for wing-fuselage configurations in incompressible potential flow. Mathematical formulations are presented for three computer programs that are employed. The first program is a conventional surface panel method for calculating the baseline singularity distribution. The second program calculates a partial derivative matrix. Each element of the matrix is the rate of change of singularity strength at one point with respect to a surface coordinate of a different point. For each baseline configuration, the calculated quantities from the first two programs establish an input file for the third. The third program calculates the surface pressure distribution and forces and moments for a series of geometry perturbations.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3528
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Inlet and airframe compatibility for a V/STOL fighter/attack aircraft with top-mounted inlets (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic force and inlet pressure data are obtained for 9.5% force and pressure models of a V/STOL fighter/attack aircraft configuration with top mounted twin inlets. Data are presented from tests conducted in the Ames Unitary Wind Tunnels at Mach numbers of 0.6, 0.9, and 1.2 at angles of attack up to 27 deg. and angles of sideslip up to 12 deg. Trimmed aerodynamic characteristics and inlet performance are compared for three different leading edge extension (LEX) configurations. The effects of wing leading and trailing-edge flaps on the inlet are also determined. Maneuver perfromance is calculated form combined force and inlet pressure data. The largest of the three LEX sizes tested gives the best airplane maneuver performance. Wing flap deflections improved inlet recovery at all Mach numbers.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84252 , A-8948 , NAS 1.15:84252
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Inlet and airframe compatibility for a V/STOL fighter/attack aircraft with top-mounted inlets (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Aerodynamic force and inlet-pressure data were obtained for 9.5% force and pressure models of a V/STOL fighter/attack aircraft configuration with top-mounted twin inlets. Data are presented from wind tunnel tests conducted at Mach numbers of 0.6, 0.9, and 1.2 at angles of attack up to 27-deg and angles of sideslip up to 12-deg. Trimmed aerodynamic characteristics and inlet performance were compared for three different leading-edge extension (LEX) configurations. The effects of wing leading- and trailing-edge flaps on the inlet were also determined. Maneuver performance was calculated from combined force and inlet-pressure data. The largest of the three LEX sizes tested gave the best airplane maneuver performance. Wing flap deflections improved inlet recovery at all Mach numbers.
    Keywords: AERODYNAMICS
    Type: International Council of the Aeronautical Sciences; Aug 22, 1982 - Aug 27, 1982; Seattle, WA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Unsteady Transonic Small Disturbance theory with strong shock waves (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Transonic Small Disturbance (TSD) theory is modified to yield steady and unsteady solutions in the case of strong shock waves (where the local Mach number ahead of the shock exceeds 1.3). The modification consists of an additional adjustable nonlinear term which allows the exact Rankine-Hugoniot shock jump relation to be satisfied at all times. The modified TSD theory is applied to steady and unsteady oscillatory transonic flows, and yields results which are in good agreement with solutions of the unsteady Euler equations, and which compare favorably with solutions of the full potential equation when shock waves are weak.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-0159 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    The NASA Langley laminar flow control airfoil experiment (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A large chord swept supercritical LFC airfoil has been constructed for NASA-Langley's research program to determine the compatibility of supercritical airfoils with suction laminarization and to establish a technology base for future transport designs. Features include a high design Mach number and shock-free flow, as well as the minimization of the laminarization suction through a choice of airfoil geometry and pressure distribution. Two suction surface concepts and a variety of hybrid suction concepts involving combinations of natural and forced laminar flow are to be investigated. The test facility has been modified to insure achievement of required flow quality and transonic interference-free flow over the yawed LFC airfoil.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-0567 , Aerodynamic Testing Conference; Mar 22, 1982 - Mar 24, 1982; Williamsburg, VA
    Format: text
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    NASA TECHNICAL REPORTS
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