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  • AERODYNAMICS  (399)
  • Cell & Developmental Biology
  • 1980-1984  (600)
  • 1930-1934  (44)
  • 1
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    Control characteristics for wrap-around fins on cruise missiles configurations (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper presents selected results of a panel loads study conducted as part of the final phase of an extensive investigation of an air-breathing missile concept employing wrap-around aerodynamic surfaces. Typical results for M = 2.36 are presented for the fin load results, plus a brief review of basic results of the previously reported tests. Vapor screen results are also discussed. The present results indicate that the fin load characteristics are nearly identical for planar and curved fins having the same projected planform and would permit the use of planar-surface predictions for supersonic speeds in the preliminary design stages of missiles employing wrap-around curved fins.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-0009 , Aerospace Sciences Meeting; Jan 12, 1981 - Jan 15, 1981; St. Louis, MO
    Format: text
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  • 2
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    Large scale model measurements of airframe noise using cross-correlation techniques (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Cross-correlation techniques are used to measure the sound radiated by wing/flap airfoil configurations in the NASA-Ames 40 x 80 ft wind tunnel using a 6.7-m semispan model with three deployed flaps. The dominant source of flap noise is identified as the flap side edges, which exceeds that radiated by the midspan region by more than 10 dB. The turbulent surface eddies at the flap side edge have scales on the order of one-half the flap chord. The installation of flap actuator fairings at the flap side edge reduces the noise radiated from that location by 10 to 15 dB. The cross-correlation technique extracts airframe noise radiated by specific surface locations from the tunnel background noise, even when the noise is 25 dB higher than the measured airframe noise level.
    Keywords: AERODYNAMICS
    Type: Acoustical Society of America; vol. 71
    Format: text
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  • 3
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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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  • 4
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    An experimental study of dynamic stall on advanced airfoil sections. Volume 1: Summary of the experiment (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The static and dynamic characteristics of seven helicopter sections and a fixed-wing supercritical airfoil were investigated over a wide range of nominally two dimensional flow conditions, at Mach numbers up to 0.30 and Reynolds numbers up to 4 x 10 to the 6th power. Details of the experiment, estimates of measurement accuracy, and test conditions are described in this volume (the first of three volumes). Representative results are also presented and comparisons are made with data from other sources. The complete results for pressure distributions, forces, pitching moments, and boundary-layer separation and reattachment characteristics are available in graphical form in volumes 2 and 3. The results of the experiment show important differences between airfoils, which would otherwise tend to be masked by differences in wind tunnels, particularly in steady cases. All of the airfoils tested provide significant advantages over the conventional NACA 0012 profile. In general, however, the parameters of the unsteady motion appear to be more important than airfoil shape in determining the dynamic-stall airloads.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84245-VOL-1 , A-8924 , NAS 1.15:84245-Vol-1 , USAAVRADCOM-TR-82-A-8-Vol-1
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  • 5
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    An experimental study of dynamic stall on advanced airfoil section. Volume 2: Pressure and force data (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experimentally derived force and moment data are presented for eight airfoil sections that were tested at fixed and varying incidence in a subsonic two dimensional stream. Airfoil incidence was varied through sinusoidal oscillations in pitch over a wide range of amplitude and frequency. The surface pressure distribution, as well as the lift, drag, and pitching moment derived therefrom, are displayed in a uniform fashion to delineate the static and dynamic characteristics of each airfoil both in and out of stall.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84245-VOL-2 , A-8925 , NAS 1.15:84245-VOL-2 , USAAVRADCOM-TR-82-A-8-VOL-2
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  • 6
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    An Experimental Study of Dynamic Stall on Advanced Airfoil Sections (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Detailed unsteady boundary layer measurements are presented for eight airfoils oscillated in pitch through the dynamic stall regime. The present report (the third of three volumes) describes the techniques developed for analysis and evaluation of the hot film and hot wire signals, offers some interpretation of the results, and tabulates all the cases in which flow reversal has been recorded.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84245-Vol-3 , A-8938 , NAS 1.15:84245-VOL-3 , USAAVRADCOM-TR-82-A-8-Vol-3
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  • 7
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    Transonic-flow computation using an explicit-implicit method (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The explicit-implicit predictor corrector method of MacCormack (1981) is applied to the analysis of flows past airfoils. By comparing results obtained with different methods and meshes, it is shown that the above method provides, after certain modifications, reasonably good predictions of inviscid and viscous flows about an airfoil. Good results are also obtained for the transonic regime if the free-stream conditions are correct and if a suitable mesh is used.
    Keywords: AERODYNAMICS
    Format: text
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  • 8
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    Effects of spanwise blowing and reverse thrust on fighter low-speed aerodynamics (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: (Previously cited in issue 07, p. 963, Accession no. A82-19203)
    Keywords: AERODYNAMICS
    Format: text
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  • 9
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    Large perturbation flow field analysis and simulation for supersonic inlets (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analysis technique for simulation of supersonic mixed compression inlets with large flow field perturbations is presented. The approach is based upon a quasi-one-dimensional inviscid unsteady formulation which includes engineering models of unstart/restart, bleed, bypass, and geometry effects. Numerical solution of the governing time dependent equations of motion is accomplished through a shock capturing finite difference algorithm, of which five separate approaches are evaluated. Comparison with experimental supersonic wind tunnel data is presented to verify the present approach for a wide range of transient inlet flow conditions.
    Keywords: AERODYNAMICS
    Type: NASA-CR-174676 , NAS 1.26:174676
    Format: application/pdf
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  • 10
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    Two-dimensional aerodynamic characteristics of an airfoil designed for two (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An airfoil designed for helicopter rotor application is investigated. The airfoil is designed to increase maximum normal force coefficient while maintaining favorable drag divergence and pitching moment characteristics. Two modifications are also tested. Maximum normal force coefficient varies from 1.14 to 0.90 at Mach numbers from about 0.35 to 0.65. Both modifications decreased drag coefficient at zero normal force coefficient for Mach numbers near drag divergence, but were less beneficial at a normal force coefficient of -0.2.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1965 , L-14825 , NAS 1.60:1965 , AVRADCOM-TR-81-B-6
    Format: application/pdf
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