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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...

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Main Authors: Muhammad Yuhendri, Yoga Farhans, Nik Mohd, Nik Ahmad Ridhwan, Mat, Shabudin, Mohd Nasir, Mohd Nazri, Othman, Norazila, Mohd Rafie, Azmin Shakrine, Azami, Muhammad Hanafi
Format: Article
Published: Aeronautical and Astronautical Society of the Republic of China 2023
Online Access:http://psasir.upm.edu.my/id/eprint/108283/
https://www.airitilibrary.com/Article/Detail/P20140627004-N202308290008-00006
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spelling my.upm.eprints.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
institution Universiti Putra Malaysia
building UPM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Putra Malaysia
content_source UPM Institutional Repository
url_provider http://psasir.upm.edu.my/
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.
format Article
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
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
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
title 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_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_sort impact of cowl deflections on scramjet intake aerodynamics with shock-on-lip condition
publisher Aeronautical and Astronautical Society of the Republic of China
publishDate 2023
url http://psasir.upm.edu.my/id/eprint/108283/
https://www.airitilibrary.com/Article/Detail/P20140627004-N202308290008-00006
_version_ 1802978792862384128
score 13.211869

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