Estimation of surface pressure distribution on a delta wing with curved leading edges in hypersonic/supersonic flow
In this paper the focus is on study of surface pressure distribution variation with angle of incidence and Mach number for hypersonic flow/Supersonic flow for a delta wing with leading edges which are curved. It is found that the surface pressure on the wing increases with increase in incidence ang...
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| المؤلفون الرئيسيون: | , , |
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| التنسيق: | مقال |
| اللغة: | English English |
| منشور في: |
NOVA Science Publishers
2016
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| الموضوعات: | |
| الوصول للمادة أونلاين: | http://irep.iium.edu.my/53341/1/paper2.pdf http://irep.iium.edu.my/53341/7/53341-Estimation%20of%20surface%20pressure%20distribution%20on%20a%20delta%20wing%20with%20curved%20leading%20edges_SCOPUS.pdf http://irep.iium.edu.my/53341/ http://www.novapublishers.com |
| الوسوم: |
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| المؤسسة: | Universiti Islam Antarabangsa Malaysia |
| اللغة: | English English |
| الملخص: | In this paper the focus is on study of surface pressure distribution variation with angle of incidence and Mach number for hypersonic flow/Supersonic flow for a delta
wing with leading edges which are curved. It is found that the surface pressure on the wing increases with increase in incidence angle and the inertia level. Results are compared for M = 8.7, 10, and 17 for delta wing with leading edge straight and curved and the results are found to be in good agreement with existing theories. |
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