Title: Aerodynamic Design of Wing for Supersonic Flight Vehicle
Authors: Mr.K.Veeranjaneyulu, Karupalli Anvesh & Dr.M.Satyanarayana Gupta
Organisation: MLR Institute of Technology and Management.
The aim of the present project is to design a wing for the given missile body-control tail surface configuration meeting the design objectives. A detailed literature survey for the related problem yielded a nominal wing loading required for this design. With this input the wing area has been selected and sized based on the design constraints. The tool for design is DATCOM semi-empirical methodology, which is based on component buildup approach and mostly used by the aerodynamic designers across globe for preliminary designs.It has been found that the configuration is able to generate enough lift at alpha less than 10° due to the fact that the huge body contribution. But the configuration was unstable by more than 1d which indicates that it cannot be controlled. The final configuration thus designed has been characterized for its operating M.A regime and analyzed resulting in a performance validation for the design and off-design requirements.
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