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On the application of boundary layer control to a slender wing supersonic airliner cruising at M = 2.2 | 305 |
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On the application of boundary layer control to a slender wing supersonic airliner cruising at M = 2.2 | 4 | 6 | 10 | 3 | 5 | 4 | 3 |
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COA_Report_157_April_1962.pdf | 168 |
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