CFD Sympo 2014 1 HIGH ANGLE OF ATTACK CHARACTERISTICS OF POWERLAW DERIVED HYPERSONIC WAVERIDER - COMPUTATIONAL STUDY S.Pradeep Roy 1 , Manoj Kumar K.Devaraj 2 , Yogendra Singh 2 , N.Balakrishnan 3 , G. Jagadeesh 4 Department of Aerospace Engineering, Indian Institute of Science, Bangalore-560012 Abstract Hypersonic waverider configurations are promising candidates for future space and defence applications as they meet the stringent demands of aerodynamic efficiency at high Mach numbers. An attempt has been made here to study the high angle of attack characteristics of such configurations at hypersonic Mach numbers using HiFUN. At high angle of attacks the simulations compares well with the Newtonian theory as the upper surface pressures are negligible compared to the lower surface pressures. The aerodynamic efficiency is maximum at 4 0 and the configuration stalls at 45 0 . Keywords: Waverider, Hypersonic, High Angle of Attack characteristics, Stall. Nomenclature α Angle of attack C D Co-efficient of Drag C Dv Co-efficient of Viscous Drag C L Co-efficient of Lift HiFUN High resolution Flowsolver on UNstructured mesh L/D Lift to Drag ratio RANS Reynolds Averaged Navier-Stokes Introduction Hypersonic cruise vehicles are the potential candidates for future space and defense applications due to their superiority over conventional vehicles in terms of speed, specific impulse, ability to evade radar, IR sensors and early warning systems. Achieving high aerodynamic efficiency in such speeds is a formidable task. Waverider's seem to be promising candidates for such demands. Waverider's are hypersonic configuration derived from known flow fields and has an attached shock all along the leading edge, eventually leading to no cross flow and higher aerodynamic efficiency at design conditions. They ride on their own shock wave, hence the term “waverider”. The concept of waverider was first proposed by Terrence Nonweiler [1] in 1963 where he used simplified models to design hypersonic configurations using flow field behind planar oblique shock wave. Since then many concepts arose such as cone-derived, viscous optimized and osculating waveriders. In 2000 Starkey et al [2] developed a power law derived wing theory model to study the lift-to-drag characteristics of power law derived waverider. Mazhul et al [3] studied the off design performance of power law derived waverider at various Mach numbers and angle of attacks (up to 21 0 ) solving 3D steady, inviscid Euler equations. 1 Project Assistant, CAd Lab : pradeeproy03@gmail.com 2 Visiting Scientist, Centre of Excellence in Hypersonic. 3 Associate Professor : nbalak@aero.iisc.ernet.in 4 Professor : jaggie@aero.iisc.ernet.in CFD Sympo 2014, Bangalore