High Altitude Transonic Aerodynamics of Supercritical Airfoil at different Turbulence Levels

N. Vinayaka; C. Akshaya; Avinash Lakshmikanthan; Shiv Pratap Singh Yadav; R. P. Sindhu

Authors

N. Vinayaka Department of AeronauticalEngineering,NitteMeenakshiInstitute of Technology, Bengaluru560064, Karnataka, India
C. Akshaya Department of AeronauticalEngineering,NitteMeenakshiInstitute of Technology, Bengaluru560064, Karnataka, India
Avinash Lakshmikanthan Department of Mechanical Engineering,Nitte Meenakshi Institute of Technology, Bengaluru 560064, Karnataka, India
Shiv Pratap Singh Yadav Department of Mechanical Engineering,Nitte Meenakshi Institute of Technology, Bengaluru 560064, Karnataka, India
R. P. Sindhu Department of Aerospace Engineering, Jain University (IIAEM), Bengaluru 562112, Karnataka, India

Keywords:

Transonic Flow, Turbulence Intensity, Supercritical airfoil, Co-efficient of lift, Normal Shock wave

Abstract

Development of the high speed business and commercial aircrafts has become a key research area due to the requirement of fast means of transport. Research on up-gradation of high subsonic flights in-tosupersonic flights is in progress. While reaching supersonic velocity, the flow has to pass through the transonic regime. This regime is in-between Mach 0.8 to Mach 1.2. A quantitative research work has already been done in this regime, but still the flow is unpredictable even in 21stcentury. Hence, these research linchpins on understanding the performance of supercritical airfoil and the normal shock wave behaviour at transonic velocity regime at high altitude (8km above sea level). A supercritical airfoil SC20412 has been chosen for this work. The airfoil is modeled two dimensionally in Ansys Design Modeller and meshed in ICEMCFD. Computational Fluid Dynamics approach was engaged for analysis. The analysis is carried out at 2% and 10% Turbulent Intensity (TI) levels at Mach 0.8 and Mach 0.9 with each at 0 and 5Angle of Attack (AoA). Post processing of the results revealedthat the Co-Efficientof Lift (CL) of the airfoil decreases as the Mach number reaches 0.9 form 0.8. Increasein AoA leads to the increase in CL. The results also showed weak Mach wave and a normal shock wave on the lower and upper surface respectively at Mach 0.8.The normal shock wave starts moving towards leading edge as the AoA increases. Shock wave started moving away from the leading edge as the Mach number increased.The shock wave moves towardsthe leading edge as the turbulence intensity increases.The variation in upstream boundary conditions of normal shock wave results in the motion of its-self towards or away from leading edge.