Flow-separation modifies the wall-pressure distribution over the vehicle surface which deteriorates the aerodynamic performance of the control surface leading to loss of control surface effectiveness. As a given flight parameter changes, multiple parameters vary across the shock and changes in separation length are due to the cumulative effect of changes in these parameters. Hence, the understanding of effect of canonical parameters affecting flow-separation is essential to justify/predict the trend observed in separation length changes with different flight parameters. Scaling of the separation length with a non-dimensional scaling parameter is carried out.

1. Rachit Singh and Krishnendu Sinha, "Shock Induced Flow-Separation in Hypersonic Intakes at Off-design Conditions," Journal of Aerospace Sciences and Technologies, Vol.71, No.2, pp.231-249, 2019.

2. Singh, R. and Sinha, K., "Shock induced flow-separation in hypersonic intakes at off-design conditions", Journal of Aerospace Sciences and Technology, 2019.

3. Singh, R. and Sinha, K., "Parametric study of factors affecting shock-induced flow separation in scramjet intakes," 20th Annual CFD Symposium, August 09-10, 2018, CSIR - National Aerospace Laboratories, Bangalore, India.

4. Vemula, J. B., Raje, P., Singh, R., Roy, S. and Sinha K., 10-11 August 2016, "Parametric study of the performance of two-dimensional Scramjet Intake", 18th Annual AeSI CFD Symposium, CSIR-National Aerospace Laboratories, Bangalore, India.

5. Sinha, K. and Singh, R. "Numerical Error in the k-ε Turbulence Model applied to Eddy-viscous Shock Waves", AIAA Journal, Volume 54, Issue 11, pp. 3676-3681, November 2016.

• B.E. in Mechanical Engineering from M.S.University of Baroda, Gujarat.
• M.E. in Mechanical Engineering form Sardar Vallabhbhaipatel Institute of Technology, Vasad, Gujarat.