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- W2332340838 abstract "The present study is aimed at designing wing planform for winged Reusable Launch Vehicle, which satisfies the required performance and aerodynamic criteria with minimum weight. A matrix of nine wing-body configurations has been selected and analyzed at typical subsonic, supersonic and hypersonic Mach numbers. Design constraints considered are wing leading edge sweep angle, touch down velocity, subsonic lift to drag ratio and pitching moment coefficient at subsonic, supersonic and hypersonic Mach numbers. Configuration fulfilling the objective without violating the design constraints has been designed independently using both graphical technique and Response Surface Methodology. The designs using the two methods match well. Longitudinal trim/ controllability analysis of the designed configuration is also carried out and the control surface deflection is within limits." @default.
- W2332340838 created "2016-06-24" @default.
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- W2332340838 date "2006-06-05" @default.
- W2332340838 modified "2023-09-26" @default.
- W2332340838 title "Wing Planform Design Optimization Using Graphical Technique and Response Surface Methodology for Winged Reusable Launch Vehicle" @default.
- W2332340838 cites W2068815710 @default.
- W2332340838 doi "https://doi.org/10.2514/6.2006-3458" @default.
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