A biconvex airfoil (see Figure 8.14) is constructed of circular arcs. We shall approximate the curve on
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A biconvex airfoil (see Figure 8.14) is constructed of circular arcs. We shall approximate the curve on the upper surface by 10 straight-line segments, as shown in Figure P8.9.
(a) Determine the pressure immediately after the oblique shock at the leading edge.
(b) Determine the Mach number and pressure on each segment.
(c) Compute the contribution to the lift and drag from each segment.
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Related Book For
Fundamentals Of Gas Dynamics
ISBN: 9781119481690
3rd Edition
Authors: Robert D Zucker, Oscar Biblarz
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