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Effect of aspect ratio variation on subsonic aerodynamics of cascade type grid fin at different gap-to-chord ratios

Published online by Cambridge University Press:  03 December 2019

M. Tripathi Open the ORCID record for M. Tripathi [Opens in a new window] ,
M.M. Sucheendran  and
A. Misra
M. Tripathi*
Affiliation:
Aerospace Engineering Defence Institute of Advanced Technology, Pune, India
M.M. Sucheendran
Affiliation:
Department of Mechanical and Aerospace Engineering Indian Institute of Technology Hyderabad, Hyderabad, India
A. Misra
Affiliation:
Aerospace Engineering Defence Institute of Advanced Technology, Pune, India
*
manish.tripathi1189@gmail.com
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Abstract

This paper dwells upon investigating the effect of aspect ratio (AR) variation on the aerodynamic performance of unconventional control surfaces called grid fins by virtue of a series of subsonic experiments on a simplified grid fin variant called the cascade fin. Wind tunnel tests were performed for different AR (variable span) grid fins. The same had been investigated for different gap-to-chord ratio (g/c) variants. Results demonstrated a tangible increase in the aerodynamic efficiency as well as stall angle reduction for higher AR. Moreover, higher AR leads to increased pitching moment, which emphasizes elevated hinge moment requirements. The study ensued the presence of higher deviation between the low AR fins, that is $AR<2$ compared to the pertinent deviations between the high AR fins, that is $AR\geq2$ . The effect associated with these variations was termed as span effect in this paper. It was established that, the deviations arising due to this phenomena were lesser for higher g/c and higher AR. The analysis of AR variation for different g/c presented a limiting value of AR reduction for stall performance enhancement. Thus, optimised selection of the g/c and AR values can lead to enhanced aerodynamic efficiency alongside an improved stalling characteristic.

Keywords

Grid finCascade finsSubsonicWind tunnelGap-to-chord ratioAspect ratio
Type
Research Article
Information
The Aeronautical Journal , Volume 124 , Issue 1274 , April 2020 , pp. 472 - 498
Copyright
© Royal Aeronautical Society 2019

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