The total temperature in the hypersonic wind tunnel test can be significantly different from that in real flight conditions, and this leads to a large discrepancy in the measurement of the boundary layer transition between ground experiment measurements and flight tests. Even at the same Mach number and Reynolds number, different wind tunnels may yield different transition data for the same model due to the total temperature effect. In this paper, the boundary layer transition on a 7° half-angle sharp cone (at a 0° angle of attack) with four freestream total temperatures is investigated using both the simulations of a local correlation-based transition model and linear stability analysis. The results show that as the freestream total temperature increases, the starting point of the transition on the sharp cone gradually moves backward and the length of the transition region decreases. The N factor of the unstable wave gradually decreases with increasing freestream total temperature, causing the transition onset to move backward. The total temperature effects on boundary transition as determined by both methods of analysis were in good agreement.
REFERENCES
1.
S.
Berry
, K.
Daryabeigi
, and K.
Wurster
, “Boundary-layer transition on X-43A
,” J. Spacecr. Rockets
47
, 922
–934
(2010
).2.
M. P.
Borg
, “Laminar instability and transition on the X-51A
,” Ph.D. thesis, Purdue University
, August 2009
.3.
Y. D.
Zhu
, X.
Chen
, J. Z.
Wu
, S. Y.
Chen
, C. B.
Lee
, and M.
Gad-el-Hak
, “Aerodynamic heating in transitional hypersonic boundary layers: Role of second-mode instability
,” Phys. Fluids
30
, 011701
(2018
).4.
W. F.
Si
, G. L.
Huang
, Y. D.
Zhu
, S. Y.
Chen
, and C. B.
Lee
, “Hypersonic aerodynamic heating over a flared cone with wavy wall
,” Phys. Fluids
31
, 051702
(2019
).5.
Z. N.
Wu
, C. Y.
Bai
, J.
Li
, Z. J.
Chen
, S. X.
Ji
, D.
Wang
, W. B.
Wang
, Y. Z.
Xu
, and Y.
Yao
, “Analysis of flow characteristics for hypersonic vehicle
,” Acta Aerodyn. Sin.
36
, 58
–85
(2015
).6.
Z. C.
Huang
, “The boundary layer transition of aerospace plane
,” J. Exp. Fluid Mech.
8
, 1
–9
(1994
).7.
P. A.
Polivanov
, A. A.
Sidorenko
, and A. A.
Maslov
, “Transition effect on shock wave/boundary layer interaction at M = 1.47
,” AIAA Paper 2015-1974, 2015
.8.
Z. G.
Zhang
, J. S.
Zhao
, Z. Y.
Peng
, X. W.
Tang
, Y. L.
Shi
, and T.
Chen
, “Research on the conversion method of aeroheating environment of hypersonic vehicle
,” in The 17th National Conference of Computational Fluid Dynamics
, 2013
.9.
T.
Schilden
, W.
Schröder
, S. C.
Ali
, A. M.
Schreyer
, J.
Wu
, and R.
Radespiel
, “Analysis of acoustic and entropy disturbances in a hypersonic wind tunnel
,” Phys. Fluids
28
, 056104
(2016
).10.
S. R.
Pate
, “Effects of wind tunnel disturbances on boundary-layer transition with emphasis on radiated noise: A review
,” AIAA Paper No. 80-0431, 1980
.11.
S. P.
Schneider
, “Developing mechanism-based methods for estimating hypersonic boundary-layer transition in flight: The role of quiet tunnels
,” Prog. Aerosp. Sci.
72
, 17
–29
(2015
).12.
S. P.
Schneider
, “Flight data for boundary-layer transition at hypersonic and supersonic speeds
,” J. Spacecr. Rockets
36
, 8
–20
(1999
).13.
E. C.
Marineau
, G.
Grossir
, A.
Wagner
, M.
Leinemann
, R.
Radespiel
, H.
Tanno
, T. P.
Wadhams
, B. C.
Chynoweth
, S. P.
Schneider
, R. M.
Wagnild
, and K. M.
Casper
, “Compilation and analysis of second-mode amplitudes on sharp cones in hypersonic wind tunnels
,” AIAA Paper 2018-0349, 2018
.14.
T. J.
Juliano
, M. P.
Borg
, and S. P.
Schneider
, “Quiet tunnel measurements of HIFiRE-5 boundary-layer transition
,” AIAA J.
53
, 832
–846
(2015
).15.
T. C.
Lin
, “The influence of laminar boundary layer transition on entry vehicle design and its performance
,” AIAA Paper 2007-309, 2007
.16.
X. L.
Li
, D. X.
Fu
, and Y. W.
Ma
, “Direct numerical simulation of hypersonic boundary layer transition over a blunt cone with a small angle of attack
,” Phys. Fluids
22
, 025105
(2010
).17.
J. T.
Lachowicz
, N.
Chokani
, and S. P.
Wilkinson
, “Boundary-layer stability measurements in a hypersonic quiet tunnel
,” AIAA J.
34
, 2496
–2500
(1996
).18.
J. F.
Kenneth
and L.
Sanjiva
, “Effect of adverse pressure gradient on high speed boundary layer transition
,” Phys. Fluids
26
, 024106
(2014
).19.
P.
Dong
, P. G.
Yan
, H. Y.
Huang
, and G. T.
Feng
, “Numerical simulation of temperature gradient influence on flat plate boundary layer transition
,” J. Propul. Technol.
29
, 527
–532
(2008
).20.
Z. Y.
Liu
and W. B.
Yang
, “Effect of temperature on high-speed boundary layer stability and transition
,” in First China Aerodynamics Conference
, 2018
.21.
J.
Blazek
, Computational Fluid Dynamics: Principles and Applications
(Elsevier
, Amsterdam, London, New York
, 2001
).22.
J. L.
Steger
and R. F.
Warming
, “Flux vector splitting for the inviscid gas dynamic equations with application to finite difference methods
,” J. Comput. Phys.
40
, 263
–293
(1981
).23.
F. T.
Eleuterio
, Riemann Solvers and Numerical Methods for Fluid Dynamics: The Riemann Problem for the Euler Equations
(Springer
, Berlin
, 1997
).24.
Z. W.
Li
, “Study on the dissipative effect of approximate Riemann solver on hypersonic heatflux simulation
,” Chin. J. Theor. Appl. Mech.
40
, 19
–25
(2008
).25.
S.
Yoon
and A.
Jameson
, “Lower-upper symmetric-Gauss–Seidel method for the Euler and Nävier–Stokes
,” AIAA J.
26
, 1025
–1036
(1988
).26.
R. B.
Langtry
, K.
Sengupta
, D. T.
Yeh
, and A. J.
Dorgan
, “Extending the γ-Reθt local correlation based transition model for crossflow effects
,” AIAA Paper 2015-2474, 2015
.27.
W. X.
Kong
, C.
Yan
, and R.
Zhao
, “γ−Reθ model research for high-speed boundary layer transition
,” Acta. Aerodyn. Sin.
31
, 120
–126
(2013
).28.
K.
Bensassi
, A.
Lani
, and P.
Rambaud
, “Numerical investigations of local correlation-based transition model in hypersonic flows
,” AIAA Paper 2012-3151, 2012
.29.
G.
Cheng
, R.
Nichols
, K. D.
Neroorkar
, and P. G.
Radhamony
. “Validation and assessment of turbulence transition models
,” AIAA Paper 2009-1141, 2009
.30.
Y. F.
Zhang
and Y. R.
Zhang
, “Calibration study of γ−Reθ transition model on Chant, a super software platform
,” in The 17th National Hypersonic Aerodynamics/Hot Academic Exchange Conference
, 2013
.31.
R.
Kimmel
, “The effects of pressure gradients on transition zone length in hypersonic boundary layers
,” J. Fluid Eng.
119
, 36
–41
(1997
).32.
B.
Khalil
, L.
Andrea
, and R.
Patrick
, “Numerical investigations of local correlation-based transition model in hypersonic flows
,” AIAA Paper 2012-3151, 2012
.33.
Y. F.
Zhang
, J.
Lei
, Y. R.
Zhang
, M. L.
Mao
, and J. Q.
Chen
, “Calibration of transition model for hypersonic numerical simulation platform
,” Acta. Aerodyn. Sin.
33
, 42
–47
(2015
).34.
S.
Fu
and L.
Wang
, “RANS modeling of high-speed aerodynamic flow transition with consideration of stability theory
,” Prog. Aerosp. Sci.
58
, 36
–59
(2013
).35.
F. R.
Menter
, R. B.
Langtry
, and S.
Völker
, “Transition modelling for general purpose CFD codes
,” Flow, Turbul. Combust.
77
, 277
–303
(2006
).36.
X.
Guo
and D. B.
Tang
, “Stability studies of compressible boundary layer flows based on PSE
,” Ph.D. thesis, Nanjing University of Aeronautics and Astronautics
, October 2009
.37.
C. H.
Su
and H.
Zhou
, “Transition prediction of hypersonic boundary layer over a blunt cone with small nose bluntness at small angle of attack and the improvement of the eN method
,” Sci. China Ser. G: Phys., Mech.
52
, 115
–123
(2009
).© 2019 Author(s).
2019
Author(s)
You do not currently have access to this content.
