Abstract
The effects of leading edge bluntness on boundary layer transition and separation have been studied experimentally. The studies have been carried out in a hypersonic gun tunnel facility at M ∞ = 8.2 and Re ∞ /cm = 9.0 × 104. The flow structure over a low aspect ratio flat plate with a full span trailing edge flap has been investigated using high speed Schlieren photography as well as surface pressure and heat transfer measurements.
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Abbreviations
- C :
-
Chapman-Rubesin constant
- Cd :
-
Leading edge drag coefficient
- C H :
-
Heat transfer coefficient q/ρ ∞ U ∞ c p (T 0 — T w )
- Cp :
-
Specific heat (isobaric)
- d :
-
Leading edge diameter
- L :
-
Hingeline length
- M :
-
Mach number
- Re :
-
Reynolds number
- T:
-
Temperature
- x :
-
Distance from the leading edge
- χ:
-
Viscous interaction parameter, \(M^3 \,\sqrt {(C/\operatorname{Re} _x )}\)
- χε :
-
ε[0.664 + 1.73(T w /T 0)]χ
- ε:
-
(γ − 1)/(γ + 1)
- γ:
-
Ratio of specific heats
- Kε :
-
M 3 C D ε (d/dx)
- β :
-
Bluntness-viscous interaction parameter χε/κ 2/3ε
- δ :
-
Flap deflection angle (°)
- δx :
-
Change in distance along the plate
- α :
-
Angle of incidence (°)
- w :
-
wall
- f :
-
flap
- O:
-
reservoir
- ∞:
-
freestream
- s :
-
Separation (in Figures 1–6)
References
Edwards CLW, Anders JB (1968) Low density, leading edge bluntness and ablation effects on wedge induced laminar boundary layer separation at moderate enthalpies in hypersonic flows. NASA TN D-4829
Jillie DW, Hopkins EJ (1961) Effect of Mach number, leading edge bluntness and sweep on boundary layer transition on a flat plate. NASA TN-D 1071
Holden M (1975) Experimental studies in shock wave — boundary layer interactions. AGARD AG-203
Lukasiewicz J (1961) Hypersonic flow blast analogy. AEDC TN-61–158
Needham DA (1965) Laminar separation in hypersonic flows. PhD thesis, University of London. See also AIAA Paper 66–455
Reshotko E, Khan MMS (1979) Stability of a laminar boundary layer on a blunted flat plate in supersonic flow — Laminar-Turbulent transition. IUTAM Symposium, Stuttgart, pp 189–200
Sanator RJ, Boccio JL, Shamshins D (1968) Effects of bluntness on hypersonic two-dimensional inlet type flows. NASA CR-1145
Townsend JC (1966) Effects of leading edge bluntness and ramp deflection angle on laminar boundary layer separation in hypersonic flow. NASA TN-D 3290
Vermeulen JP, Simeonides G (1992) Parametric study of shock wave/boundary layer interactions over 2-D compression corners at Mach 6. VKI TN-181.
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© 1995 Springer-Verlag Berlin Heidelberg
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Kumar, D., Stollery, J.L. (1995). Effects of Leading-Edge Bluntness on Control Flap Effectiveness at Hypersonic Speeds. In: Brun, R., Dumitrescu, L.Z. (eds) Shock Waves @ Marseille I. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-78829-1_6
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DOI: https://doi.org/10.1007/978-3-642-78829-1_6
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