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  • AERODYNAMICS  (111)
  • 1980-1984  (110)
  • 1945-1949  (1)
  • 1935-1939
  • 1984  (110)
  • 1948  (1)
  • 1
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    Asymptotic methods for wind tunnel wall corrections at transonic speed (1984)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The effort to develop classical methods to compute wall interference at transonic speeds is outlined. The two-dimensional theory and three-dimensional development are discussed. Also, some numerical application of the two-dimensional work are indicated. The basic advantages of the asymptotic theory are noted.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 193-203
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A new consistent spatial differencing scheme for the transonic full-potential equation (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 5, p. 585, Accession no. A83-16678
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 22; 1027-103
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Technology developments for laminar boundary layer control on subsonic transport aircraft (1984)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The development of laminar flow technology for commercial transport aircraft is discussed and illustrated in a review of studies undertaken in the NASA Aircraft Energy Efficiency (ACEE) program since 1976. The early history of laminar flow control (LFC) techniques and natural laminar flow (NLF) airfoil designs is traced, and the aims of ACEE are outlined. The application of slotted structures, composites, and electron beam perforated metals in supercritical LFC airfoils, wing panels, and leading edge systems is examined; wind tunnel and flight test results are summarized; studies of high altitude ice effects are described; and hybrid (LFC/NLF designs are characterized. Drawings and photographs are provided.
    Keywords: AERODYNAMICS
    Type: AGARD Improvement of Aerodynamic Performance Through Boundary Layer Control and High Lift Systems; 13 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental Results for a Flapped Natural-laminar-flow Airfoil with High Lift/drag Ratio (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experimental results have been obtained for a flapped natural-laminar-flow airfoil, NLF(1)-0414F, in the Langley Low-Turbulence Pressure Tunnel. The tests were conducted over a Mach number range from 0.05 to 0.40 and a chord Reynolds number range from about 3.0 x 10(6) to 22.0 x 10(6). The airfoil was designed for 0.70 chord laminar flow on both surfaces at a lift coefficient of 0.40, a Reynolds number of 10.0 x 10(6), and a Mach number of 0.40. A 0.125 chord simple flap was incorporated in the design to increase the low-drag, lift-coefficient range. Results were also obtained for a 0.20 chord split-flap deflected 60 deg.
    Keywords: AERODYNAMICS
    Type: NASA-TM-85788 , NAS 1.15:85788
    Format: application/pdf
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  • 5
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    Boundary layer transition effects on flow separation around V/STOL engine inlets at high incidence (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Numerical methods for calculating laminar and turbulent boundary layer development around vertical-short take off and landing engine inlets at high incidence angles are investigated. Various transition models were compared and evaluated in calculations off flow separation bound inside the inlet. Results of the transition effects on the boundary layer characteristics at onset of separation for two types of engine inlet geometries are presented. Some of the numerical results are compared with existing wind-tunnel test data for scaled inlet models to demonstrate the effects of transition models in the numerical scheme. The effects of transition modeling on the boundary layer development are illustrated for typical engine operating conditions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0432
    Format: text
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  • 6
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    Multiple steady states for characteristic initial value problems (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The time dependent, isentropic, quasi-one-dimensional equations of gas dynamics and other model equations are considered under the constraint of characteristic boundary conditions. Analysis of the time evolution shows how different initial data may lead to different steady states and how seemingly anamolous behavior of the solution may be resolved. Numerical experimentation using time consistent explicit algorithms verifies the conclusions of the analysis. The use of implicit schemes with very large time steps leads to erroneous results.
    Keywords: AERODYNAMICS
    Type: NASA-CR-172486 , ICASE-84-57 , NAS 1.26:172486
    Format: application/pdf
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  • 7
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    High Reynolds number tests of the cast 10-2/DOA 2 airfoil in the Langley 0.3-meter transonic cryogenic tunnel, phase 2 (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel tests of an advanced technology airfoil, the CAST 10-2/DOA 2, were conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel (0.3-m TCT). This was the third of a series of tests conducted in a cooperative airfoil research program between the National Aeronautics and Space Administration and the Deutsche Forschungsund Versuchsanstalt fur Luft- und Raumfahrt e. V. For these tests, temperature was varied from 270 K to 110 K at pressures from 1.5 to 5.75 atmospheres. Mach number was varied from 0.60 to 0.80, and the Reynolds number (based on airfoil chord) was varied from 2 to 20 million. The aerodynamic data for the 7.62 cm chord airfoil model used in these tests is presented without analysis. Descriptions of the 0.3-m TCT, the airfoil model, the test instrumentation, and the testing procedures are included.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86273 , NAS 1.15:86273
    Format: application/pdf
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  • 8
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    Experimental investigation of the aerodynamic effects of distributed spanwise blowing on a fighter configuration (1948)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The results of wind tunnel tests at NASA Langley targeted at the performance and configurational characteristics of 0.1 and 0.13 scale model spanwise blowing (SWB) jet wing concepts are reported. The concept involves redirection of engine compressor bleed air to provide SWB at the fuselage-wing juncture near the wing leading edge. The tests covered the orientation of the outer panel nozzles, the effects of SWB operation on the performance of leading and trailing edge flaps and the effects of SWB on lateral stability. The trials were run at low speeds and angles of attack from 24-45 deg (landing). Both lift and longitudinal stability improved with the SWB, stall and leading edge vortex breakdown were delayed and performance increased with the SWB rate. Lateral stability was degraded below 20 deg angle of attack while instabilities were delayed above 20 deg due to roll damping.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-2195
    Format: text
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  • 9
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    A hybrid explicit-implicit numerical algorithm for the three-dimensional compressible Navier-Stokes equations (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Previously cited in issue 5, p. 582, Accession no. A83-16593
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 22; 1056-106
    Format: text
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  • 10
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    Numerical calculations of complex Mach reflection (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Numerical simulations of the interaction of a planar blast wave with a compression ramp are presented. The split coefficient matrix (SCM) method in conjunction with boundary shock and floating discontinuity-fitting procedures was employed to obtain the time-asymptotic solutions of the two-dimensional, unsteady Euler equations. The solutions were computed for the complex Mach reflection (CMR) regime of the shock diffraction problem in an attempt to explore the basic physical process governing the evolution of an incipient second Mach stem and the associated topological changes. Numerical results were obtained for shock diffraction over a 40 degree ramp with varying incident shock Mach numbers. The validity of the present approach has been substantiated by experimental observations and earlier numerical calculations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-1679
    Format: text
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