Effect of aspect ratio with roll moment derivative of a delta wing in supersonic flow
In this paper attention is focussed on study of effect of Aspect ratio of the wing on roll moment derivatives at various angle of attack and Mach number for a Supersonic flow. It is been observed that there is a linear increment in rolling moment derivative with aspect ratio as well as with Angle...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
| Published: |
IRA Publications
2016
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| Subjects: | |
| Online Access: | http://irep.iium.edu.my/50991/ http://irep.iium.edu.my/50991/ http://irep.iium.edu.my/50991/3/Asha_Crasta_-IJAER.pdf |
| Summary: | In this paper attention is focussed on study of effect of Aspect ratio of the wing on roll moment derivatives at
various angle of attack and Mach number for a Supersonic flow. It is been observed that there is a linear
increment in rolling moment derivative with aspect ratio as well as with Angle of attack. The reason behind this
being rolling moment derivative is a linear function of aspect ratio and angle of attack. The requirement for the
validity of the present theory is the attachment of the shock at the leading edge of the wing. Whereas, in the case
of detached shock wave, this theory is not valid. |
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