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On the aerodynamic characteristics of thin slab delta wings at hypersonic speeds - part 2: effect of wing geometry

Published online by Cambridge University Press:  04 July 2016

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

We report our findings on the aerodynamic characteristics of thin slab delta wings at hypersonic speeds. We have tested wings with three sweeps (76°,70° and 65°) and four t/c ratios (0·04, 0·053, 0·066 and 0·10) using a special thin three-component balance. To date, the wing with tic of 0·040 is the thinnest wing ever tested without lee-side body at any hypersonic Mach number. The study was carried out at Mach number of 8·2, Reynolds number of 2·13 x 106 and incidence of -4° to 12°. In general, for any given t/c ratio, the increase in sweep decreased the CN whereas increased CM and CA. A possible explanation, for the effect of sweep, is given using the pressure data available in the literature. We also observed that for the sweeps considered, the t/c does not have any effect on CN and CL but increasing t/c increased CM and CA, reduced (L/D)max and moved the Xcp upstream. Blunt slab delta wings are shown to possess a unique property, wherein the CD increases with increase in sweep at higher sweep angles. This property also reflects in the (L/D) characteristics. Furthermore, the slab delta wings does not exhibit the classical CLα behaviour of sharp delta wings given in the literature. An empirical correlation has been developed to correlate CAo over a wide range of Mach number, t/c and sweep. Linearised theory has been shown to be useful in predicting the (L/D)max at Mach numbers as high as 20, for a wide range of t/c and sweep back angle.

Type
Research Article
Information
The Aeronautical Journal , Volume 104 , Issue 1042 , December 2000 , pp. 597 - 614
Copyright
Copyright © Royal Aeronautical Society 2000 

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References

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