Abstract
It is the purpose of this Part 2 of the paper to examine the two devices for improvement proposed in Part 1 numerically. We call these two devices Method 1 and Method 2. Downwash angle is calculated of a steady rectangular wing assuming a simple loading. It is shown that Method 1 makes it possible to greatly reduce the computing time in cases of oscillating wings, and that remarkable improvement in convergence with respect to the number of spanwise integration points is obtained by Method 2.
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More From: Journal of the Japan Society for Aeronautical and Space Sciences
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