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Probing Within the Boundary Layer of an Airfoil by Using the Wind Numerical Code
| AUTHOR | Administration (Nasa), National Aeronaut |
| PUBLISHER | Independently Published (08/06/2020) |
| PRODUCT TYPE | Paperback (Paperback) |
Description
A detailed boundary layer investigation of an NACA 0012 airfoil was made by applying the WIND code at the NASA Glenn Research Center. Structured C-grids of selected configurations were fitted around the airfoil. Grids with dense spacing to capture the boundary layer provided for obtaining accurate results in this region. Concurrent with the boundary layer investigation, contour plots of overall performance of the airfoil were also obtained. A Mach number of 0.80, a Reynolds number of 4,000,000, and a zero angle of attack were set to correspond with numerical and experimental investigations reported in the literature, for comparison with the overall performance. The results were favorable for both the boundary layer investigations and the performance. As WIND evolves, it is intended to run WIND using unstructured grids to compare such results with the current structured grid results. Cavicchi, Richard H. Glenn Research Center NASA/TM-2004-213221, E-14728 WBS 708-90-21 AIRFOILS; BOUNDARY LAYERS; STRUCTURED GRIDS (MATHEMATICS); MACH NUMBER; REYNOLDS NUMBER; ZERO ANGLE OF ATTACK; CONTOURS
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Product Format
Product Details
ISBN-13:
9798672785622
Binding:
Paperback or Softback (Trade Paperback (Us))
Content Language:
English
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Page Count:
40
Carton Quantity:
102
Product Dimensions:
8.50 x 0.08 x 11.02 inches
Weight:
0.26 pound(s)
Country of Origin:
US
Subject Information
BISAC Categories
Reference | Research
Reference | Space Science - General
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A detailed boundary layer investigation of an NACA 0012 airfoil was made by applying the WIND code at the NASA Glenn Research Center. Structured C-grids of selected configurations were fitted around the airfoil. Grids with dense spacing to capture the boundary layer provided for obtaining accurate results in this region. Concurrent with the boundary layer investigation, contour plots of overall performance of the airfoil were also obtained. A Mach number of 0.80, a Reynolds number of 4,000,000, and a zero angle of attack were set to correspond with numerical and experimental investigations reported in the literature, for comparison with the overall performance. The results were favorable for both the boundary layer investigations and the performance. As WIND evolves, it is intended to run WIND using unstructured grids to compare such results with the current structured grid results. Cavicchi, Richard H. Glenn Research Center NASA/TM-2004-213221, E-14728 WBS 708-90-21 AIRFOILS; BOUNDARY LAYERS; STRUCTURED GRIDS (MATHEMATICS); MACH NUMBER; REYNOLDS NUMBER; ZERO ANGLE OF ATTACK; CONTOURS
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