M.S.R. Chandra Murty

Bio: M.S.R. Chandra Murty is an academic researcher from Defence Research and Development Laboratory. The author has contributed to research in topics: Computational fluid dynamics & Turbulence. The author has an hindex of 4, co-authored 5 publications receiving 37 citations.

Numerical simulation of angular injection of hydrogen fuel in scramjet combustor

Abstract: Angular injection of hydrogen fuel in a scramjet combustor is explored numerically. Three-dimensional Navier–Stokes equations with turbulence and combustion models are solved using commercial computational fluid dynamics software. Both infinitely fast kinetics and single-step finite rate H2–air kinetics are used to find out the effect of chemical kinetics in the thermochemical behaviour of the flow field. Grid independence of the results is demonstrated and gridconvergence index-based error estimate provided. k-ω turbulence model performs better, in comparison to k–ϵ and shear stress transport models, in predicting the surface pressure. Single-step finite rate chemistry (SSC) performs extremely well in predicting the flow features in the combustor. Computed temperature and species mole fraction and wall pressure distributions with SSC match better with the experimental results compared to fast chemistry calculation and detailed chemistry calculation of other workers. It has been observed that simple chemistry can describe H2–air reaction in scramjet combustor reasonably well.

Numerical Simulation of Supersonic Combustion with Parallel Injection of Hydrogen Fuel

Abstract: Thermochemical exploration of mixing and combustion of parallel hydrogen injection into supersonic vitiated air stream in a divergent duct is presented. Three-dimensional Navier Stokes equations along with twoequation turbulence models and Eddy dissipation concept (EDC)-based combustion models are solved using commercial CFD software. Chemical reaction for H2-air system is modelled by two different simple chemical kinetic schemes namely; infinitely fast rate kinetics as well as the single-step finite rate kinetics. Grid convergence of the solution is demonstrated and a grid convergence index-based error estimate has been provided. Insight into the mixing and combustion of high-speed turbulent reacting flow is obtained through the analysis of various thermochemical variables. Very good comparisons are obtained for the exit profiles for various fluid dynamical and chemical variables for the mixing case. For reacting case, the comparison between the experimental and the numerical values are reasonable. Parametric studies were carried out to study the effect of different turbulence models and turbulent Schmidt numbers. It is seen that Wilcox k-w turbulence model performed better than the other two-equation turbulence models in its class. Strong dependence of flow behaviour on turbulent Schmidt number was observed. The results indicate that simple chemical kinetics is adequate to describe the H2-air reaction in the scramjet combustor. Defence Science Journal, 2010, 60(5), pp.465-475 , DOI:http://dx.doi.org/10.14429/dsj.60.57

A Novel CFD Method to Estimate Heat Transfer Coefficient for High Speed Flows

Abstract: Accurate prediction of surface temperature of high speed aerospace vehicle is very necessary for the selection of material and determination of wall thickness. For aerothermal characterisation of any high speed vehicle in its full trajectory, it requires number of detailed computational fluid dynamics (CFD) calculations with different isothermal calculations. From the detailed CFD calculations for different flow conditions and geometries, it is observed that heat transfer coefficients scale with the difference of adiabatic wall temperature and skin temperature. A simple ‘isothermal method’, is proposed to calculate heat flux data with only two CFD simulations one on adiabatic condition and other on isothermal condition. The proposed methodology is validated for number of high speed test cases involving external aerodynamic heating as well as high speed combusting flow. The computed heat fluxes and surface temperatures matches well with experimental and flight measured values.