Impact of cowl deflections on scramjet intake aerodynamics with shock-on-lip condition
The design of the Scramjet intake has a greater effect on the overall performance of the engine than any other component. By adjusting the leading edge's sharpness, length, and deflection, air compression can be maximized. To enhance overall pressure recovery, a shock-on-lip condition is freque...
| Main Authors: | , , , , , , |
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| Format: | Article |
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Aeronautical and Astronautical Society of the Republic of China
2023
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| Online Access: | http://psasir.upm.edu.my/id/eprint/108283/ |
| _version_ | 1848865121333411840 |
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| author | Muhammad Yuhendri, Yoga Farhans Nik Mohd, Nik Ahmad Ridhwan Mat, Shabudin Mohd Nasir, Mohd Nazri Othman, Norazila Mohd Rafie, Azmin Shakrine Azami, Muhammad Hanafi |
| author_facet | Muhammad Yuhendri, Yoga Farhans Nik Mohd, Nik Ahmad Ridhwan Mat, Shabudin Mohd Nasir, Mohd Nazri Othman, Norazila Mohd Rafie, Azmin Shakrine Azami, Muhammad Hanafi |
| author_sort | Muhammad Yuhendri, Yoga Farhans |
| building | UPM Institutional Repository |
| collection | Online Access |
| description | The design of the Scramjet intake has a greater effect on the overall performance of the engine than any other component. By adjusting the leading edge's sharpness, length, and deflection, air compression can be maximized. To enhance overall pressure recovery, a shock-on-lip condition is frequently applied to a standard supersonic inlet. The design of a two-ramp mixed compression intake for freestream Mach numbers 5.5 to 7 is examined in this paper, taking into account the shock-on-lip condition in all analyses. Using inviscid numerical models, the effects of the various deflections of the cowl are investigated. Due to the shock-on-lip effect, the captured mass flow rate decreases linearly as the isolator area and height decrease with increasing Mach number. As the Mach number increases, stronger shocks result in higher pressure and temperature ratios. Additionally, the total pressure recovery, which decreases with increasing Mach number, is positively influenced by the angle at which the cowl is deflected. Due to the significant increase in isolator height brought on by the low Mach number shockwave crossing point, shock-on-lip was still present and the results for Mach 5.5 were less than ideal. |
| first_indexed | 2025-11-15T13:59:40Z |
| format | Article |
| id | upm-108283 |
| institution | Universiti Putra Malaysia |
| institution_category | Local University |
| last_indexed | 2025-11-15T13:59:40Z |
| publishDate | 2023 |
| publisher | Aeronautical and Astronautical Society of the Republic of China |
| recordtype | eprints |
| repository_type | Digital Repository |
| spelling | upm-1082832024-06-13T08:51:10Z http://psasir.upm.edu.my/id/eprint/108283/ Impact of cowl deflections on scramjet intake aerodynamics with shock-on-lip condition Muhammad Yuhendri, Yoga Farhans Nik Mohd, Nik Ahmad Ridhwan Mat, Shabudin Mohd Nasir, Mohd Nazri Othman, Norazila Mohd Rafie, Azmin Shakrine Azami, Muhammad Hanafi The design of the Scramjet intake has a greater effect on the overall performance of the engine than any other component. By adjusting the leading edge's sharpness, length, and deflection, air compression can be maximized. To enhance overall pressure recovery, a shock-on-lip condition is frequently applied to a standard supersonic inlet. The design of a two-ramp mixed compression intake for freestream Mach numbers 5.5 to 7 is examined in this paper, taking into account the shock-on-lip condition in all analyses. Using inviscid numerical models, the effects of the various deflections of the cowl are investigated. Due to the shock-on-lip effect, the captured mass flow rate decreases linearly as the isolator area and height decrease with increasing Mach number. As the Mach number increases, stronger shocks result in higher pressure and temperature ratios. Additionally, the total pressure recovery, which decreases with increasing Mach number, is positively influenced by the angle at which the cowl is deflected. Due to the significant increase in isolator height brought on by the low Mach number shockwave crossing point, shock-on-lip was still present and the results for Mach 5.5 were less than ideal. Aeronautical and Astronautical Society of the Republic of China 2023 Article PeerReviewed Muhammad Yuhendri, Yoga Farhans and Nik Mohd, Nik Ahmad Ridhwan and Mat, Shabudin and Mohd Nasir, Mohd Nazri and Othman, Norazila and Mohd Rafie, Azmin Shakrine and Azami, Muhammad Hanafi (2023) Impact of cowl deflections on scramjet intake aerodynamics with shock-on-lip condition. Journal of Aeronautics, Astronautics and Aviation, 55 (spec.3). 461 - 468. ISSN 1990-7710 https://www.airitilibrary.com/Article/Detail/P20140627004-N202308290008-00006 10.6125/JoAAA.202309_55(3S).05 |
| spellingShingle | Muhammad Yuhendri, Yoga Farhans Nik Mohd, Nik Ahmad Ridhwan Mat, Shabudin Mohd Nasir, Mohd Nazri Othman, Norazila Mohd Rafie, Azmin Shakrine Azami, Muhammad Hanafi Impact of cowl deflections on scramjet intake aerodynamics with shock-on-lip condition |
| title | Impact of cowl deflections on scramjet intake aerodynamics with shock-on-lip condition |
| title_full | Impact of cowl deflections on scramjet intake aerodynamics with shock-on-lip condition |
| title_fullStr | Impact of cowl deflections on scramjet intake aerodynamics with shock-on-lip condition |
| title_full_unstemmed | Impact of cowl deflections on scramjet intake aerodynamics with shock-on-lip condition |
| title_short | Impact of cowl deflections on scramjet intake aerodynamics with shock-on-lip condition |
| title_sort | impact of cowl deflections on scramjet intake aerodynamics with shock-on-lip condition |
| url | http://psasir.upm.edu.my/id/eprint/108283/ http://psasir.upm.edu.my/id/eprint/108283/ http://psasir.upm.edu.my/id/eprint/108283/ |