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  • 2000-2004  (3)
  • 1
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    Visualization of In-Flight Flow Phenomena Using Infrared Thermography (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Infrared thermography was used to obtain data on the state of the boundary layer of a natural laminar flow airfoil in supersonic flight. In addition to the laminar-to-turbulent transition boundary, the infrared camera was able to detect shock waves and present a time dependent view of the flow field. A time dependent heat transfer code was developed to predict temperature distributions on the test subject and any necessary surface treatment. A commercially available infrared camera was adapted for airborne use in this application. Readily available infrared technology has the capability to provide detailed visualization of various flow phenomena in subsonic to hypersonic flight regimes.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA/TM-2000-209027 , NAS 1.15:209027 , H-2422 , International Symposium on Flow Visualization; Aug 22, 2000 - Aug 25, 2000; Edinburgh; Solomon Islands
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Prediction of Flows about Forebodies at High-Angle-of-Attack Dynamic Conditions (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: A Reynolds-average Navier Stokes method developed for rotorcraft type of flow problems is applied for predicting the forces and moments of forebody models at high-angle-of-attack dynamic conditions and for providing insight into the flow characteristics at these conditions. Wind-tunnel results from rotary testing on generic forebody models conducted by NASA Langley and DERA are used for comparison. This paper focuses on the steady-state flow problem.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Symposium on Advanced Flow Management. Part A: Vortex Flows and High Angle of Attack for Military Vehicles. Part B: Heat Transfer and Cooling in Propulsion and Power Systems; RTO-MP-069(I)-Pt-A-B
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Aero-Mechanical Design Methodology for Subsonic Civil Transport High-Lift Systems (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: In today's highly competitive and economically driven commercial aviation market, the trend is to make aircraft systems simpler and to shorten their design cycle which reduces recurring, non-recurring and operating costs. One such system is the high-lift system. A methodology has been developed which merges aerodynamic data with kinematic analysis of the trailing-edge flap mechanism with minimum mechanism definition required. This methodology provides quick and accurate aerodynamic performance prediction for a given flap deployment mechanism early on in the high-lift system preliminary design stage. Sample analysis results for four different deployment mechanisms are presented as well as descriptions of the aerodynamic and mechanism data required for evaluation. Extensions to interactive design capabilities are also discussed.
    Keywords: Aircraft Design, Testing and Performance
    Type: Aerodynamic Design and Optimisation of Flight Vehicles in a Concurrent Multi-Disciplinary Environment; 7-1 - 7-12; RTO-MP-35
    Format: text
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    NASA TECHNICAL REPORTS
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