In:
The Aeronautical Journal, Cambridge University Press (CUP), Vol. 104, No. 1042 ( 2000-12), p. 597-614
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 10 6 and incidence of -4° to 12°. In general, for any given t/c ratio, the increase in sweep decreased the C N whereas increased C M and C A . 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 C N and C L but increasing t/c increased C M and C A , reduced (L/D) max and moved the X cp upstream. Blunt slab delta wings are shown to possess a unique property, wherein the C D 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 C Lα behaviour of sharp delta wings given in the literature. An empirical correlation has been developed to correlate C Ao 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 of Medium:
Online Resource
ISSN:
0001-9240
,
2059-6464
DOI:
10.1017/S0001924000096846
Language:
English
Publisher:
Cambridge University Press (CUP)
Publication Date:
2000
detail.hit.zdb_id:
2378167-1
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