Numerical Characterisation of Supersonic Exhaust Diffusers

Solid Propulsion is widely used in Missile and Space applications. Accurate prediction of Specific impulse (Isp) is important for design of Solid rocket motor. These predictions can be done using empirical relations. Obtaining these empirical relations require large amount of data. The renowned aerospace organizations use their own code for prediction. These codes are not open source and also developing a code requires big team effort with challenges of verification and validations. The present work is aimed at developing numerical model for prediction of Specific Impulse. The model is validated against the experimental data of static test of solid rocket motor taken from literature.

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Comparative Analysis of Aerodynamic Characteristics of F16 and F22 Combat Aircraft using Computational Fluid Dynamics

Malik

Tevatia

2021

Def. Sc. J.

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This paper presents the computational investigation of air flow over an aircraft at realistic speeds while demonstrating the importance of extending the existing analysis to the complete airplane and how pivotal it is in improving its in-flight performance. The study is done for F16 and F22 aircraft using ANSYS Fluent (19.2) to obtain pressure distribution, shear stress distribution and temperature variation on the complete surface of the aircraft. Since the front section of the aircraft is prone to direct initial impact of surrounding environment, this portion is also examined. Here, as the speed is doubled from Mach 1 to Mach 2, a rise in the value of all the three variables is noticed for the F16 aircraft, whereas the pressure distribution for F22 aircraft shows strange behaviour for the highest speed (Mach 2). On comparing the results over the whole surface, it is seen that F16 experiences smaller pressure (29% lower for Mach 1 and 30% for Mach 2), temperature (9.5% lower for Mach 1 and 30% for Mach 2) and shear stress relative to F22 and the stress shows a huge change (90% lower for Mach 1 and 83% for Mach 2). Results of the present study imply that the design of the aircraft highly influences its performance as the parameters discussed touch their limits.

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Numerical Characterisation of Supersonic Exhaust Diffusers

Abstract: Rocket motors that are designed to operate at high altitudes need a nozzle with a large expansion ratio to maximize the thrust at much lower atmospheric pressure than that of the sea level pressure. Accurate performance of these nozzles cannot be obtained when static tested on ground.

Cited by 3 publications

References 10 publications

Simulation studies on aerodynamic features of Eurofighter Typhoon and Dassault Rafale combat aircraft

Simulation studies on aerodynamic features of Eurofighter Typhoon and Dassault Rafale combat aircraft

Prediction of solid rocket motor performance characteristics using computational fluid dynamics and validation with experimental data

Comparative Analysis of Aerodynamic Characteristics of F16 and F22 Combat Aircraft using Computational Fluid Dynamics

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