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Finite Volume Numerical Methods for Aeroheating Rate Calculations from Infrared Thermographic Data

Finite Volume Numerical Methods for Aeroheating Rate Calculations from Infrared Thermographic Data


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About the Book

The use of multi-dimensional finite volume heat conduction techniques for calculating aeroheating rates from measured global surface temperatures on hypersonic wind tunnel models was investigated. Both direct and inverse finite volume techniques were investigated and compared with the standard one-dimensional semi-infinite technique. Global transient surface temperatures were measured using an infrared thermographic technique on a 0.333-scale model of the Hyper-X forebody in the NASA Langley Research Center 20-Inch Mach 6 Air tunnel. In these tests the effectiveness of vortices generated via gas injection for initiating hypersonic transition on the Hyper-X forebody was investigated. An array of streamwise-orientated heating striations was generated and visualized downstream of the gas injection sites. In regions without significant spatial temperature gradients, one-dimensional techniques provided accurate aeroheating rates. In regions with sharp temperature gradients caused by striation patterns multi-dimensional heat transfer techniques were necessary to obtain more accurate heating rates. The use of the one-dimensional technique resulted in differences of 20% in the calculated heating rates compared to 2-D analysis because it did not account for lateral heat conduction in the model.


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Product Details
  • ISBN-13: 9781289286002
  • Publisher: Bibliogov
  • Publisher Imprint: Bibliogov
  • Height: 246 mm
  • Weight: 95 gr
  • ISBN-10: 1289286000
  • Publisher Date: 06 Aug 2013
  • Binding: Paperback
  • Spine Width: 2 mm
  • Width: 189 mm


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Finite Volume Numerical Methods for Aeroheating Rate Calculations from Infrared Thermographic Data
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