Base Pressure Control using Quarter Circle Rib in a Suddenly Expanded Duct at Screech Prone Mach Number M = 1.8

Authors

  • Zakir Ilahi Chaudhary Department of Mechanical Engineering Automobile, M. H. Saboo Siddik College of Engineering, Mumbai 400008, India
  • Ambareen Khan School of Aerospace Engineering, Universiti Sains Malaysia, 11600 Gelugor, Pulau Pinang, Malaysia
  • Sher Afghan Khan Department of Mechanical & Aerospace Engineering, Faculty of Engineering, International Islamic University Malaysia, Gombak, 53100 Kuala Lumpur, Malaysia
  • Khizar Ahmed Pathan Department of Mechanical Engineering, CSMSS Chh. Shahu College of Engineering, Aurangabad, Maharashtra 431001, India

DOI:

https://doi.org/10.37934/cfdl.17.8.6095

Keywords:

Base drag, screech prone Mach number, L/D ratio, level of expansion

Abstract

Occurrence of sudden expansion is widespread in the defence and automobile industry. At the blunt base of the fuselage, missiles, projectiles and aircraft bombs, the flow gets separated at the base and forms low-pressure recirculation, leading to a significant increase in the base drag. This paper addresses how this low base pressure at the base can be controlled. In this study, quarter circle ribs are used as a control mechanism to regulate the base pressure in a suddenly expanded flow of area ratio 4.84, Mach M = 1.8 for nozzle pressure ratios (NPRs) ranging from 3 to 11 at various rib locations in the range from 11 mm, 22mm, 33 mm, 44 mm and 66mm for duct length ranging from L = 1D to 6D. Results show for 11 mm rib location and 1 mm rib radius, there is a declining trend in the base till nozzle pressure ratio of 6 and for further increases in the expansion level, there is a progressive increase in the base pressure ratio. The highest base pressure value is 2 for a 4 mm rib radius at the highest simulated nozzle pressure ratio. This trend continues for 22 mm rib locations. With a further shift in the rib location, there is a considerable increase in the base pressure ratio. These values are 2.5, 3 and 3.75 for rib locations at 33 mm, 44 mm and 66 mm for a rib radius of 4 mm at the highest level of under-expansion. It is seen that even though the effectiveness of the 1 mm rib radius was nil for all the rib locations except when the rib is located at 66 mm. When a quarter circle rib of radius 1 mm is used, there is a significant increase in the base pressure and base suction is nearly zero. This study is a technology demonstration and the database created from this study can be used to design aerospace vehicles. It will be beneficial at the initial design stage as a wind tunnel test is costly.

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Author Biographies

Zakir Ilahi Chaudhary, Department of Mechanical Engineering Automobile, M. H. Saboo Siddik College of Engineering, Mumbai 400008, India

chzakirilahi@gmail.com

Ambareen Khan, School of Aerospace Engineering, Universiti Sains Malaysia, 11600 Gelugor, Pulau Pinang, Malaysia

khanambareen5@gmail.com

Sher Afghan Khan, Department of Mechanical & Aerospace Engineering, Faculty of Engineering, International Islamic University Malaysia, Gombak, 53100 Kuala Lumpur, Malaysia

sakhan@iium.edu.my

Khizar Ahmed Pathan, Department of Mechanical Engineering, CSMSS Chh. Shahu College of Engineering, Aurangabad, Maharashtra 431001, India

kn.pathan@gmail.com

References

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[13] Fakhruddin, Ahmad‘Afy Ahmad, Fharukh Ahmed Ghasi Mahaboobali, Ambareen Khan, Mohammad Nishat Akhtar, Sher Afghan Khan and Khizar Ahmad Pathan. "Analysis of Base Pressure Control with Ribs at Mach 1.2 using CFD Method." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 123, no. 1 (2024): 108-143. https://doi.org/10.37934/arfmts.123.1.108143

[14] Khan, Ambareen, Parvathy Rajendran, Junior Sarjit Singh Sidhu, S. Thanigaiarasu, Vijayanandh Raja and Qasem Al-Mdallal. "Convolutional neural network modeling and response surface analysis of compressible flow at sonic and supersonic Mach numbers." Alexandria Engineering Journal 65 (2023): 997-1029. https://doi.org/10.1016/j.aej.2022.10.006

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[16] Shaikh, Javed S., Krishna Kumar, Khizar A. Pathan and Sher A. Khan. "Analytical and computational analysis of pressure at the nose of a 2D wedge in high speed flow." Advances in aircraft and spacecraft science 9, no. 2 (2022): 119-130.

[17] Crasta, Asha, Khizer Ahmed Pathan and Sher Afghan Khan. "Numerical simulation of surface pressure of a wedge at supersonic Mach numbers and application of design of experiments." Journal of advanced research in applied mechanics 101, no. 1 (2023): 1-18. https://doi.org/10.37934/aram.101.1.118

[18] Crasta, Asha, Khizar Ahmed Pathan and Sher Afghan Khan. "Analytical and Numerical Simulation of Surface Pressure of an Oscillating Wedge at Hypersonic Mach Numbers and Application of Taguchi's Method." Journal of Advanced Research in Applied Sciences and Engineering Technology 30, no. 1 (2023): 15-30. https://doi.org/10.37934/araset.30.1.1530

[19] Shaikh, Javed Shoukat, Khizar Ahmed Pathan, Krishna Kumar and Sher Afghan Khan. "Effectiveness of Cone Angle on Surface Pressure Distribution along Slant Length of a Cone at Hypersonic Mach Numbers." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 104, no. 1 (2023): 185-203. https://doi.org/10.37934/arfmts.104.1.185203

[20] Shaikh, Javed S., Krishna Kumar, Khizar A. Pathan and Sher A. Khan. "Computational analysis of surface pressure distribution over a 2d wedge in the supersonic and hypersonic flow regimes." Fluid Dynamics & Materials Processing 19, no. 6 (2023). https://doi.org/10.32604/fdmp.2023.025113

[21] Chaudhari, Pavan Bhaskar, Rachayya Arakerimath, Khizar Ahmed Pathan and Sher Afghan Khan. "Comparative Experimental Analysis and Performance Optimization of Single-Cylinder DI and HCCI Engine with Series Catalytic Converters." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 121, no. 1 (2024): 173-187. https://doi.org/10.37934/arfmts.121.1.173187

[22] Jain, Yogeshkumar, Vijay Kurkute, Sagar Mane Deshmukh, Khizar Ahmed Pathan, Ajaj Rashid Attar and Sher Afghan Khan. "The Influence of Plate Fin Heat Sink Orientation under Natural Convection on Thermal Performance: An Experimental and Numerical Study." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 114, no. 2 (2024): 118-129. https://doi.org/10.37934/arfmts.114.2.118129

[23] Khalil, Shaikh Sohel Mohd, Rai Sujit Nath Sahai, Nitin Parashram Gulhane, Khizar Ahmed Pathan, Ajaj Rashid Attar and Sher Afghan Khan. "Experimental Investigation of Local Nusselt Profile Dissemination to Augment Heat Transfer under Air Jet Infringements for Industrial Applications." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 112, no. 2 (2023): 161-173. https://doi.org/10.37934/arfmts.112.2.161173

[24] Shaikh, Sohel Khalil, Khizar Ahmed Pathan, Zakir Ilahi Chaudhary, B. G. Marlpalle and Sher Afghan Khan. "An investigation of three-way catalytic converter for various inlet cone angles using CFD." CFD Letters 12, no. 9 (2020): 76-90. https://doi.org/10.37934/cfdl.12.9.7690

[25] Shaikh, Sohel Khalil, Khizar Ahmed Pathan, Zakir Ilahi Chaudhary and Sher Afghan Khan. "CFD analysis of an automobile catalytic converter to obtain flow uniformity and to minimize pressure drop across the monolith." CFD Letters 12, no. 9 (2020): 116-128. https://doi.org/10.37934/cfdl.12.9.116128

[26] Kale, Dipak, Rachayya Arakerimath, Khizar Ahmed Pathan and Sher Afghan Khan. "Investigation on Water Erosion Behavior of Ti-based Metal Matrix Composite: Experimental Approach." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 122, no. 2 (2024): 71-82. https://doi.org/10.37934/arfmts.122.2.7182

[27] Sheikh, Fahim Rahim, Suresh Pandurang Deshmukh, Purushottam Ardhapurkar, Khizar Ahmed Pathan, Sohel Khalil Shaikh and Sher Afghan Khan. "Modeling and Experimental Validation of NePCM-Nanofluid-Based PVT System." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 122, no. 1 (2024): 205-222. https://doi.org/10.37934/arfmts.122.1.205222

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[35] Khan, Ambareen, Nurul Musfirah Mazlan and Mohd Azmi Ismail. "Analysis of flow through a convergent nozzle at Sonic Mach Number for Area Ratio 4." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 62, no. 1 (2019): 66-79.

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Published

2025-02-28

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