The Computational Study on the Aerodynamics Behaviour of the Hypersonic Vehicles

Abstract

Current air-breathing hypersonic flight( AHF) technology programs are primarily concentrated on developing flight test vehicles and functional prototypes that incorporate airframe- integrated scramjet machines. A pivotal aspect of making AHF feasible and effective falsehoods in the design of its control systems.still, the unique dynamic characteristics of air- breathing hypersonic flight vehicles( AHFVs), combined with the aerodynamic complications at hypersonic pets, pose significant challenges for system modeling and regulator development. also, the expansive speed variations during operation and the limited vacuity of a comprehensive flight dynamics database introduce substantial misgivings and factory parameter variations, further complicating the AHF modeling and control process. In this exploration paper we will study about the Basic dynamic characteristics of AHFVs, colorful fine models developed for the flight dynamics of AHFVs and about the hypersonic aerodynamics. The important part of computational fluid dynamics in ultramodern hypersonic exploration is underlined. We\'ll also bandied about the computational study on the AHFVs with different anaylsis which include inflow separation, shock commerce and etc.

Introduction

Overview of Hypersonic Aerodynamics

Hypersonic flow generally refers to airflows at Mach numbers greater than 5, but no strict boundary exists; relevant phenomena may begin to appear from Mach 3–7, depending on the body shape and flow conditions.

Key Characteristics of Hypersonic Flow:

• Thin Shock Layer:
  At high speeds, shock waves form very close to the body, creating a thin shock layer. This leads to complexities like shock-boundary layer interactions, particularly significant at low Reynolds numbers. In high Reynolds numbers, inviscid assumptions allow for simplified modeling such as shock-layer theory and Newtonian approximations.

• Entropy Layer:
  Near blunt bodies, the shock-induced entropy gradient results in an entropy layer that interacts with the boundary layer and introduces vorticity. This layer complicates accurate boundary-layer modeling due to varying external conditions.

• Surface Pressure Estimation:
  Unlike supersonic flows, hypersonic surface pressures are better predicted by Newtonian flow theory, which assumes all flow momentum normal to a surface is lost upon impact. The theory does not include Mach number, but Modified Newtonian theory refines it by incorporating stagnation pressure, Mach number, and gas properties (γ).

2. Computational Study of a Hypersonic Vehicle (Mach 5)

A simulation was performed on a hypersonic vehicle using SolidWorks Flow Simulation to analyze key flow parameters at Mach 5. The vehicle remains stationary while airflow moves at a high speed in the negative Z-direction.

Key Input Parameters:

• Velocity: 1715 m/s (approx. Mach 5)

• Ambient Pressure: 101325 Pa

• Ambient Temperature: 293.2 K

• Gravity: -9.81 m/s² in Y-direction

• Flow Type: Turbulent

• Wall Condition: Adiabatic (no heat loss through walls)

Computational Domain:

• Dimensions: 0.096 m (X), 0.063 m (Y), 0.388 m (Z)

Mesh Settings:

• Automatic initial mesh with resolution level 4

Global Goals Monitored:

1. Total Pressure

2. Fluid Temperature

3. Total Temperature

4. Mach Number

5. Turbulent Energy

6. Heat Flux

7. Heat Transfer Rate

These metrics help assess the thermal and fluid dynamics performance under hypersonic conditions.

Conclusion

This computational study on the aerodynamics of hypersonic vehicles provides insight into key flow characteristics at Mach 5, including pressure variations, velocity changes, and temperature distributions. The results demonstrate the significance of computational fluid dynamics in understanding flow separation, shock interactions, and boundary layer behavior. The findings also highlight the role of factors such as entropy layers and thin shock layers in the aerodynamic performance of hypersonic vehicles. Future studies can further refine the computational model by incorporating more complex turbulence models and experimental validation to enhance accuracy in predicting hypersonic flow behavior.

References

[1] AIAA -84-1518, A survey of Modern Research in Hypersonic Aerodynamic by Department of Aerospace Engineering , University of Maryland Park, Maryland 20742. [2] Truitt, R.W , Hypersonic Aerodynamic , Ronald Press, New York , 1959. [3] Anderson, J.D (2007). Hypersonic Flow , Handbook of fluid dynamics and fluid machinery , 629-670. [4] Hypersonic Flow – John Anderson , JR University of Maryland College Park , MD. [5] Hypersonic Aerodynamic – Configuration Aerodynamic CH-11 [7131/16] [6] Journal of Fluid and structure 19(2004)681-712- Aeroelastic analysis of hypersonic vehicles by P.P Friedmann , J.J Mc Namara, B.J Thuruthimattam , I. Nydick. [7] The Aeronautical Journey- A cae study on the aerodynamic heating of a hypersonic vehicle – volume 116 NO 1183. [8] 12th AIAA International Space planes and hypersonic systems and technologies 15-19 December 2003 , Norfolk , Virginia. Flight Dynamics and Control of air- breathing Hypersonic Vehicles: Review and New Directions by Baris Fidan, Maj Mirmirani and Petros A. Iannou.

Copyright

Copyright © 2025 Isha Verma, Prince Chauhan, Jenifer Beg. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.