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Computational study of the cavity flow over sharp nose cone in supersonic flow

Author

Listed:
  • F. Pish

    (Department of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran)

  • Tran Dinh Manh

    (#x2020;Institute of Research and Development, Duy Tan University, Da Nang 550000, Vietnam)

  • M. Barzegar Gerdroodbary

    (#x2021;Department of Mechanical Engineering, Babol Noshirvani University of Technology, Babol, Iran)

  • Nguyen Dang Nam

    (#x2020;Institute of Research and Development, Duy Tan University, Da Nang 550000, Vietnam)

  • Rasoul Moradi

    (#xA7;Department of Chemical Engineering, School of Engineering & Applied Science, Khazar University, Baku, Azerbaijan)

  • Houman Babazadeh

    (#xB6;Department for Management of Science and Technology Development, Ton Duc Thang University, Ho Chi Minh City, Vietnam∥Faculty of Environment and Labour Safety, Ton Duc Thang University, Ho Chi Minh City, Vietnam)

Abstract

Heat and drag reduction on the nose cone is a significant issue for increasing the speed of the supersonic vehicles. In this paper, computational fluid dynamic method is applied to investigate the thermal and drag coefficient on the sharp nose cone with different cavity shapes. In order to simulate our model, the CFD method with SST turbulence model is applied to study the flow feature and temperature distribution in the vicinity of the nose body. The effect of depth and length of the cavity on the thermal characteristic of the nose cone is comprehensively investigated. In addition, the influence of the number of the cavity in the thermal performance of the main body is studied. According to our results, increasing the length of the cavity highly efficient for the reduction of the drag at Mach = 3. As the Mach number is increased to 3, the number of the cavity becomes a significant role and it is observed that case 9 with four cavities is more efficient. Obtained results also show that increasing the cavity depth declines the temperature on the main body. Our findings confirm that the main source of the expansion is the edge of the cavity.

Suggested Citation

  • F. Pish & Tran Dinh Manh & M. Barzegar Gerdroodbary & Nguyen Dang Nam & Rasoul Moradi & Houman Babazadeh, 2020. "Computational study of the cavity flow over sharp nose cone in supersonic flow," International Journal of Modern Physics C (IJMPC), World Scientific Publishing Co. Pte. Ltd., vol. 31(06), pages 1-12, June.
    • Handle: RePEc:wsi:ijmpcx:v:31:y:2020:i:06:n:s0129183120500795
    DOI: 10.1142/S0129183120500795
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    Citations

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    Cited by:

    1. Ma, Lianghua & Liu, Xiaoliang & Liu, Haoyang & Alizadeh, As'ad & Shamsborhan, Mahmoud, 2023. "The influence of the struts on mass diffusion system of lateral hydrogen micro jet in combustor of scramjet engine: Numerical study," Energy, Elsevier, vol. 279(C).
    2. Ben Ali, Naim & Basem, Ali & Ghodratallah, Pooya & Singh, Pradeep Kumar & jasim, Dheyaa J. & Sultan, Abbas J. & Eladeb, Aboulbaba & Kolsi, Lioua & El-Shafay, A.S., 2024. "The usage of non-aligned multi-circular winding injectors for efficient fuel mixing inside the scramjet engine," Energy, Elsevier, vol. 298(C).
    3. Li, Yaohui & Zhu, Guanghui & Chao, Yanpu & Chen, Liangbin & Alizadeh, As'ad, 2023. "Comparison of the different shapes of extruded annular nozzle on the fuel mixing of the hydrogen jet at supersonic combustion chamber," Energy, Elsevier, vol. 281(C).
    4. Wei, Dechen & Jiao, Yuanyuan & Zhang, Ning & Gao, Hongyang & Yu, Hao, 2024. "The role of annular 2-lobe nozzle in a strut injection system on the mechanism of fuel distribution at a scramjet engine," Energy, Elsevier, vol. 301(C).
    5. Huang, Dian, 2024. "Using extruded circular multi-injectors to improve fuel jet mixing and distribution in combustion chambers of scramjet," Energy, Elsevier, vol. 288(C).
    6. Peng, Yeping & Barzegar Gerdroodbary, M. & Sheikholeslami, M. & Shafee, Ahmad & Babazadeh, Houman & Moradi, R., 2020. "Mixing enhancement of the multi hydrogen fuel jets by the backward step," Energy, Elsevier, vol. 203(C).
    7. Wei, Dechen & Jiao, Yuanyuan & Zhang, Ning & Fan, Yukun, 2023. "Effect of shock generator on fuel mixing in an annular single lobe transverse nozzle at the supersonic combustion chamber of a scramjet engine using computational fluid dynamics," Energy, Elsevier, vol. 283(C).
    8. Dai, Zuocai & Zou, Yunhe & Chow, Limeng, 2024. "The role of the shock generator on the mixing performance of hydrogen jet released from the extruded transverse 3-lobe nozzle in a scramjet engine," Energy, Elsevier, vol. 288(C).

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