Wind tunnel tests at mach numbers up to 2.80 to determine the effects of changing spanwise volume distribution on a slender, cambered ogee wing
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Wind tunnel tests at mach numbers up to 2.80 to determine the effects of changing spanwise volume distribution on a slender, cambered ogee wing
T. A. Cook
URI:
https://reports.aerade.cranfield.ac.uk/handle/1826.2/817
Date:
1965
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Aeronautical Research Council Current Papers
[1393]
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