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- W2332521309 abstract "Steady-state Computational Fluid Dynamic (CFD) analyses using GASP version 3 flow solver has be431 pezformed for a missile configuration with side thruster at given full scale f&e flight~conditions and quarter scale wind tunnel model conditic~ls with similar computaticmal grids. The given jet exit conditions for both cases were required to have the same thrust az&icients, which is an empirical scaling law used in the jet interaction (JI) cmmuui~. The purpose of this analysis is to examine aud compare the integrated axial and normal forces and pitching moment obtained fi-om the two computations to determine if they are indeed identical. It was found that the axial aud ncmnal force coefficients differ by 10 and 3 percent, respectively, and that the pitching moment coefficients vary by 28 percent. The differences in axial force between the two cases is attributed to the difference of Reynolds numbs between them and thecause of pitchiig moment diffezence is due the Closeness of the pitching and the pressure centers. The scaling law of constant thrust coefficient is satisfactory in present study. However, in a separated study, it was found that in addition to keep the thrust coefficients the same, one must also keep the jet Machnumbers the same for both cases in or& to obtain correct andbest sin&&y." @default.
- W2332521309 created "2016-06-24" @default.
- W2332521309 creator A5062533137 @default.
- W2332521309 date "1999-01-11" @default.
- W2332521309 modified "2023-10-16" @default.
- W2332521309 title "Analysis of the scaling effects for missile configuration with lateral thruster" @default.
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- W2332521309 doi "https://doi.org/10.2514/6.1999-810" @default.
- W2332521309 hasPublicationYear "1999" @default.
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