Date

2002

Author

Başoğlu, Osman

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Panel methods are extensively used in aerodynamic analysis of missiles in early stages of their development. An existing TUBİTAK-SAGE panel code is modified and improved for routine and more efficient calculation of the aerodynamic coefficients of various missile configurations at subsonic and supersonic flight conditions. Particularly, the poor convergence, user unfriendliness and poor output characters of this code have been improved by modifying and adding new routines to it. Now the code with an incorporated graphical user interface converges faster, gives more useful aerodynamic information, including the hinge moments of the control surfaces and surface pressure distribution, and produces ready-to-visualize outputs. The modified 111and improved code is called the TÜBİTAK SAGE Vortex Lattice Method (TS- VLM). Previously unstudied capabilities and applicability range of this code are also explored in this thesis by carrying out extensive benchmarking studies of the code by solving various missile configurations, such as Sparrow, Sidewinder, NASA TM X -3310, and the generic wrap-around finned missiles. Comparisons of the results with available experimental data indicate that the code can generally compute the lift and normal force coefficients accurately at small to moderate angles of attack (0 to 15 degrees), and the pitching moment coefficient accurately at only small angles of attack (0 to 5 degrees), but Ms to compute these at higher angles. It is also proved that some aerodynamic coefficients related to the rotational motions of the missiles such as Magnus moment, roll and pitch damping coefficients can be computed accurately for supersonic Mach numbers.

Subject Keywords

Panel methods, Vortex lattice method, Missile aerodynamics, Rotational effects in missile aerodynamics

URI

https://hdl.handle.net/11511/12861

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Graduate School of Natural and Applied Sciences, Thesis