Delta Wing

The delta wings in modern days large operated in jet fighter aircraft. The tremendous changes in the wing design of delta wing. Using 2-D and 3-D model analysis for different delta wing configuration will be analyzed Using ANSYS-FLUENT. 

The simulation of different configuration will be carried out using k-Ω (SST) model for sonic, transonic, supersonic conditions. 

The optimum performance carried out of different configuration to be analyzed & calculating wave drag by manual technique. Compare different delta wing configuration by graphs which plotted in Microsoft word.

INJECTORS USED IN SCRAMJET COMBUSTOR

Using 2-D model, the cold flow analysis of scramjet engine will be carried out using ANSYS-Fluent. The simulation for different parameters such as cold flow performance, injection of hydrogen in combustor and process of combustion by addition of heat will be compared for two different types of injectors. i.e. planer strut injector and ojival body injector. The turbulence model used for simulation will be k-ε . The overall performance of both injectors will be analysed on the basis of above mentioned parameters.

THEORETICAL AND NUMERICAL ANALYSIS OF SR-71'S INLET FOR DIFFERENT MACH REGIME

The objective of this research project is to carry out theoretical and numerical simulation of SR-71’s inlet for different Mach no. such as 1.7, 2.0, 2.5, 3.0 and 3.2. The SR-71’s inlet was having a variable spike geometry, which helps in sufficient airflow within the engine at supersonic speed and in pressure recovery. 

Modelling and numerical analysis are being carried out in ANSYS-ICEM AND FLUENT. To validate the theoretical values/results, the computational analysis for the same Mach no, will be done.

 The work is to be carried out to observe the changes across the shock in the inlet of SR-71. Additionally, stagnation pressure recovery calculation will also be done for the prescribed range of supersonic Mach no’s.