Thermal Design of Mach 8 Nozzle for Hypersonic wind Tunnel

Abstract

The wind tunnel forms important aspect of testing of bodies or space vehicle. In the present study Mach 8 nozzle for hypersonic wind tunnel is thermally analysed. The analysis is formed under high temperature conditions as expected in space. The material of nozzle has been tested for high temperature with and without throat cooling conditions. The analysis is performed for alternative cycle of heating and cooling of nozzle. It was found for the conditions of analysis, the temperatures in the material of nozzle are within the acceptable limits.

Introduction

I. INTRODUCTION

The hypersonic wind tunnel is used to perform wind tunnel simulation studies in the hypersonic range of Mach numbers. Figure 1 shows typical schematic of hypersonic wind tunnel. Such wind tunnels are used for testing by space agencies.  The system uses air as working fluid, which is usually heated to high temperatures in a storage air heater before passing through the nozzle. The nozzle used in experimental setup is subjected to high temperatures.

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Conclusion

The Mach 8 Nozzle thermal analysis has been performed. It is found that maximum temperatures attained by all the components during the blow down operation and cooling operation are well within the material safe limits.

References

[1] ANSYS reference material [2] Fundamentals of Heat and Mass Transfer, Frank P. Incorpera, David P. Dewitt, Fourth Edition. [3] Thermal Properties of Metals, ASM International, First Edition, 2002

Copyright

Copyright © 2024 Dr. Rambir Bhadouriya. 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.