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- W2321816110 abstract "Experimental results obtained from an investigation of aerodynamic characteristics of a cruciform missile in subsonic flow are presented. The data, obtained from wind tunnel tests of an instrumented pressure model of a cruciform missile, are used to quantitatively determine fin-fin interference effects on a cruciform missile when it is arbitrarily rolled and pitched. Results show that fin-fin interference effects are present at all roll angles, and are generally most significant on the inboard sections of each fin. Additionally, the suitability of an analytical technique based on planar lifting surface theory to accurately model the flow field is determined by comparison with experimental fin pressure distributions and with sectional normal farce coefficientsNomenclature b wing span" @default.
- W2321816110 created "2016-06-24" @default.
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- W2321816110 date "1987-03-24" @default.
- W2321816110 modified "2023-09-23" @default.
- W2321816110 title "An investigation of the aerodynamic characteristics of a cruciform missile in subsonic flow" @default.
- W2321816110 cites W2123319341 @default.
- W2321816110 doi "https://doi.org/10.2514/6.1987-143" @default.
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