Transonic Flow Past Morphed Wing
Keywords:
3-D Aerofoil, Control surface, Lift coefficient, Pressure difference coefficient, Induced drag, Lagrange multipliers, Morphing, Transonic FlowAbstract
Attempt is made to optimise a wing profile to reduce induced drag in the presence of fixed control surface region, and thereafter transonic flow is progressed over this morphed profile to analyse the presence of shock waves. The displacement of shock wave with increasing Mach number is studied. Encouraging results are obtained. The computer programs are developed in FORTRAN language, and Gfortran complier of Fedora-12 Operating System is used to run these programs. Fedora-12 is supported on LINUX platform of VMware and is an open licence that is available for free-download. The programs are run on a 64 bit double precision Laptop.
References
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2. Rajesh Senthil Kumar T, Balaramraja VS. Aerodynamics of discreet location camber morphing airfoils in low Reynolds numbers flows. Indian Journal of Science and Technology 2017; 10(10).
3. Vasista S, Tung L, Wong K. Realisation of morphing wings: a multidisciplinary challenge. Journal of Aircraft 012; 49(1).
4. Fincham JHS, Friswell MI. Aerodynamic optimization of a camber morphing airfoil. Aerospace Science and Technology 2015; 43.
5. Gupta SC. GENMAP: Computer Code for Mission Adaptive Profile Generation. Journal of Aircraft 1988; 25(8).
6. Gupta SC. Aerodynamic optimisation of a camber morphing 3-D aerofoil in the presence of trailing edge flap deflection. Journal of Advance Research in Aeronautics and Space Sciences 2016; 3(4).
7. Ayers TG, Hallissy JB. Historical background and design evolution of transonic aircraft technology supercritical wing. 1981.
Published
2019-01-05
Issue
Section
Research Article
