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On the aerodynamic characteristics of thin slab delta wings at hypersonic speeds — part 1: interference of lee side bodies

Published online by Cambridge University Press:  04 July 2016

R. Ramesh ,
M. A. Ramaswamy ,
B. Vasudevan  and
A. Prabhu
R. Ramesh
Affiliation:
Indian Institute of Science, Bangalore, India
M. A. Ramaswamy
Affiliation:
Indian Institute of Science, Bangalore, India
B. Vasudevan
Affiliation:
Indian Institute of Science, Bangalore, India
A. Prabhu
Affiliation:
Indian Institute of Science, Bangalore, India
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Abstract

An experimental investigation on the interference effect of lee-side balance housing bodies on the longitudinal aerodynamic characteristics of thin slab delta wings has been made using a special and novel thin three-component balance. This study has been conducted using wings with a t/c of 0.053 and sweep of 76°, 70° and 65° for three different lee-side bodies viz:Body (A), Body (B) and Body (C) of which Body (C) is the smallest. The testing was carried out at Mach number of 8·2, Reynolds number of 2·13 ˘ 106 and incidence of –4° to 12°. For the smallest body (Body (C)) tested, at the incidence at which this body first goes into the aerodynamic shadow of the wing (α = 6·5°), the difference in CN, CA, CM and L/D between the wing-body and the plain wing is around by 22%, 12%, 75% and 35% respectively. This difference decreases with increase in incidence and at the highest angle-of-attack up to which testing was done (α = 12°), the. corresponding values of CN, CA, CM and L/D are around 9%, 12%, 15% and 4% respectively. Contrary to the assumption in the literature pertinent to force measurements on thin slab delta wings, the interference of the lee-side bodies are found to be appreciable even after they come into the aerodynamic shadow of the wing.

Type
Research Article
Information
The Aeronautical Journal , Volume 104 , Issue 1041 , November 2000 , pp. 561 - 567
Copyright
Copyright © Royal Aeronautical Society 2000 

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References

1. Bertram, M.H. and Everhart, P.E. An experimental study of the pressure and heat-transfer distribution on a 70° sweep slab delta wing in hypersonicflow, NASA TR R-153, 1962.Google Scholar
2. Witcofski, R.D. and Marcum, D.C. Effect of thickness and sweep angle on the longitudinal aerodynamic characteristics of slab delta plan-forms at Mach number of 20, NASA TN D-3459, 1966.Google Scholar
3. Gorenbukh, P.I. Aerodynamic fineness of a plane delta wing with rounded off edges at hypersonic velocities, Fluid Mechanics, Soviet Research, 1990, 19, pp 18–23.Google Scholar
4. Whitehead, A.H. and Keyes, J.W. Flow phenomena and separation over delta wings with trailing edge flaps at Mach 6, AIAA J, 1968, 6, pp 2380–2387.Google Scholar
5. Cross, E.J. and Hankey, W.L. Investigation of the lee-ward side of a delta wing at hypersonic speeds, J Spacecraft and Rockets, 1969, 6, pp 185–190.Google Scholar
6. Whitehead, A.H. Effect of vortices on delta wing lee-side heating at Mach 6, AIAA J, 1970, 8, pp 599–600.Google Scholar
7. Rao, D.M. and Whitehead, A.H. Lee-side vortices on delta wings at hypersonic speeds, AIAA J, 1972, 10, pp 1458–1465.Google Scholar
8. Dunavant, J.C., Narayana, K.Y. and Walberg, G. A survey of lee-side and heat transfer on delta planform configurations, AIAA paper 76–118, 1976.Google Scholar
9. Yegna Narayan, K. Lee side flow field and heat transfer of a delta wing at M = 10, AIAA J, 1978, 10, pp 160–165.Google Scholar
10. Yegna Narayan, K. and Seshadri, S.N. Types of flow on the lee-side of delta wings, Progress in Aerospace Science, 1997, 33, pp 167–257.Google Scholar
11. Vasudevan, B., Ramaswamy, M.A. and Prabhu, A. Description of IISc hypersonic wind tunnel, FM Report No 92FM-3, 1992.Google Scholar
12. Ramesh, R., Ramaswamy, M.A. and Vasudevan, B. Thin flat internal strain gauge balance for testing slab delta wing models at hypersonic speeds, IEEE-ICIASF-1995, pp 18.1–18.6.Google Scholar
13. Ramesh, R. Aerodynamic Characteristics of Thin Slab Delta Wings at Hypersonic Speeds — Effect of wing geometry and flaps, PhD Thesis, 1999, Dept of Aerospace Eng, Indian Institute of Science.Google Scholar
14. Kline, S.J. and McClintock, F.A. Describing uncertainties in single-sample experiments, Mechanical Engineering, January 1953, pp 3–8.Google Scholar