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  • Other Sources  (185)
  • AERODYNAMICS  (93)
  • METEOROLOGY AND CLIMATOLOGY  (60)
  • AIRCRAFT PROPULSION AND POWER
  • Cell & Developmental Biology
  • 1980-1984  (183)
  • 1955-1959  (2)
  • 1935-1939
  • 1982  (183)
  • 1959  (2)
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  • 1980-1984  (183)
  • 1955-1959  (2)
  • 1935-1939
Year
  • 11
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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
  • 12
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    A Computer Code for Swirling Turbulent Axisymmetric Recirculating Flows in Practical Isothermal Combustor Geometries (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A primitive pressure-velocity variable finite difference computer code was developed to predict swirling recirculating inert turbulent flows in axisymmetric combustors in general, and for application to a specific idealized combustion chamber with sudden or gradual expansion. The technique involves a staggered grid system for axial and radial velocities, a line relaxation procedure for efficient solution of the equations, a two-equation k-epsilon turbulence model, a stairstep boundary representation of the expansion flow, and realistic accommodation of swirl effects. A user's manual, dealing with the computational problem, showing how the mathematical basis and computational scheme may be translated into a computer program is presented. A flow chart, FORTRAN IV listing, notes about various subroutines and a user's guide are supplied as an aid to prospective users of the code.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-3442
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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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
  • 14
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    Effects of diabatic heating on the ageostrophic circulation of an upper tropospheric jet streak (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Interaction between the mass circulation within a mesoscale convective complex (MCC) and a direct mass circulation in the entrance region of an upper tropospheric polar jet streak was examined within the isentropic structure to investigate mechanisms responsible for linking these two scales of motion. The results establish that latent heating in the MCC modifies the direct mass circulation in the jet streak entrance region through the diabatically induced components of ageostrophic motion analyzed within isentropic coordinates. Within the strong mesoscale mass circulation of each MCC, strong horizontal mass flux convergence into the MCC at low levels is balanced by strong horizontal mass flux divergence away from the convergence at upper levels. Locations of large diabatic heating rates correspond well to the MCC position for each case; diabatic heating forces the upward vertical branch for the mesoscale mass circulation.
    Keywords: METEOROLOGY AND CLIMATOLOGY
    Type: NASA-CR-3497 , M-369
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 15
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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
  • 16
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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
  • 17
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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
  • 18
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    Impact of satellite data on large-scale circulation statistics as determined from GLAS analyses during FGGE-SOP-1 (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study using the analyses produced from the assimilation cycle of parallel model runs that both include and withhold satellite data was undertaken. The analyzed state of the atmosphere is performed using data from a certain test period during the first Special Observing Period (SOP) of the Global Weather Experiment (FGGE).
    Keywords: METEOROLOGY AND CLIMATOLOGY
    Type: NASA-CR-170578 , NAS 1.26:170578
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 19
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    Rotor redesign for a highly loaded 1800 ft/sec tip speed fan. 3: Laser Doppler velocimeter report (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Laser Doppler velocimeter (LDV) techniques were employed for testing a highly loaded, 550 m/sec (1800 ft/sec) tip speed, test fan stage, the objective to provide detailed mapping of the upstream, intrablade, and downstream flowfields of the rotor. Intrablade LDV measurements of velocity and flow angle were obtained along four streamlines passing through the leading edge at 45%, 69%, 85%, and 95% span measured from hub to tip, at 100% of design speed, peak efficiency; 100% speed, near surge; and 95% speed, peak efficiency. At the design point, most passages appeared to have a strong leading edge shock, which moved forward with increasing strength near surge and at part speeds. The flow behind the shock was of a complex mixed subsonic and supersonic form. The intrablade flowfields were found to be significantly nonperiodic at 100% design speed, peak efficiency.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-167954 , NAS 1.26:167954 , PWA-5523-122
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 20
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    The use of VAS satellite data in weather analysis, prediction and diagnosis (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Imagery available with the Goes satellite visible-IR spin-scan radiometer (VISSR) atmospheric sounders (VAS) are examined in terms of mid- and low-tropospheric moisture sensing and mesoscale soundings. The VAS can be operated in a Dwell Sounding mode (DS) involving preprogrammed scanning of a specific area using any number of combinations of 12 channels between 4-15 microns. A second, multi-spectral imaging mode (MSI) comprises operation of two IR channels simultaneously when time constraints are in effect. Case studies are presented to demonstrate the effectiveness of VAS imagery for characterizing mesoscale moisture conditions when identifying severe storms. The moisture patterns of the upper and lower troposphere are made visible, and a 6.7 micron channel image can be overlaid on a low level moisture field to delineate fields of potential instability.
    Keywords: METEOROLOGY AND CLIMATOLOGY
    Format: text
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    NASA TECHNICAL REPORTS
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