Two blunt trailing edge airfoil sections were tested in a transonic wind tunnel and their aerodynamic characteristics compared with those of a conventional NACA 64-106 section previously tested under identical conditions. The two blunt sections used a segmented trailing edge geometry to minimize their base drag. This segmented trailing edge geometry consisted of isolated rectangular blocks protruding downstream from the base with splitter plates spanning the spaces between the blocks. Both blunt sections had superior transonic stability, greater resistance to separation, and greater bending strength than the NACA section. One of the blunt sections also had less drag than the NACA section over the whole test range of lift coefficients for a significant portion of the transonic Mach number range. (Author)
Transonic Wind Tunnel Tests on Two Blunt Trailing Edge Aerofoils
1974
29 pages
Report
Keine Angabe
Englisch
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