HYPERSONIC MODEL TESTING IN A SHOCK TUNNEL

被引：4
|
作者：
OLIVIER, H [1 ]
GRONIG, H [1 ]
LEBOZEC, A [1 ]
机构：
[1] DASSAULT AVIAT,F-78141 VELIZY VILLACOUBL,FRANCE
来源：
AIAA JOURNAL | 1995年 / 33卷 / 02期
关键词：
Hypersonic aerodynamics;
D O I：
10.2514/3.12429
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
A shock tunnel is used to perform tests at hypersonic flow conditions including weak real gas effects. Pressure and heat nux distributions are measured around typical re-entry configurations. From these data c(p) values and Stanton numbers are deduced. For constant Mach and Reynolds number the experimental results achieved indicate a strong influence of the total temperature on the Stanton number distribution. For the results presented this behavior is mainly based on entropy layer and viscous interaction effects. A correlation function which takes into account these effects correlates the Stanton numbers achieved for different now conditions and in different wind tunnels fairly well.
引用
收藏
页码：262 / 265
页数：4
相关论文
共 50 条
  • [41] Visualization of Shock Wave Phenomenon around a Sharp Cone Model at Hypersonic Mach Number in a Shock Tunnel using High Speed Schlieren Facility
    Saiprakash, M.
    SenthilKumar, C.
    Sunil, G. K.
    Rampratap, S. P.
    Shanmugam, V
    Balu, G.
    JOURNAL OF APPLIED FLUID MECHANICS, 2019, 12 (02) : 461 - 468
  • [42] Review of hypersonic research investigations in IISc shock tunnel (HST1)
    Reddy, NM
    Nagashetty, K
    Jagadeesh, G
    Reddy, KPJ
    SADHANA-ACADEMY PROCEEDINGS IN ENGINEERING SCIENCES, 1996, 21 (pt 6): : 741 - 773
  • [43] Shock stand-off distance visualization in hypersonic shock tunnel using electrical discharge technique
    Nagashetty, K
    Saifuddin, KS
    Saravanan, S
    Gurumurthy, KS
    Reddy, KPJ
    24TH INTERNATIONAL CONGRESS ON HIGH-SPEED PHOTOGRAPHY AND PHOTONICS, 2001, 4183 : 674 - 681
  • [44] Shock tunnel study of spiked aerodynamic bodies flying at hypersonic Mach numbers
    Menezes, V
    Saravanan, S
    Reddy, KPJ
    SHOCK WAVES, 2002, 12 (03) : 197 - 204
  • [45] LOW DENSITY STAGNATION POINT HEAT TRANSFER MEASUREMENTS IN THE HYPERSONIC SHOCK TUNNEL
    WILSON, MR
    WITTLIFF, CE
    ARS JOURNAL, 1962, 32 (02): : 275 - 276
  • [46] FAST TEMPERATURE-MEASUREMENT BY INFRARED LINE SCANNING IN A HYPERSONIC SHOCK TUNNEL
    HENCKELS, A
    MAURER, F
    OLIVIER, H
    GRONIG, H
    EXPERIMENTS IN FLUIDS, 1990, 9 (05) : 298 - 300
  • [47] Soft Computing Based Force Recovery Technique for Hypersonic Shock Tunnel Tests
    Pallekonda, Ramesh Babu
    Nanda, Soumya Ranjan
    Dwivedy, Santosha K.
    Kulkarni, Vinayak
    Menezes, Viren
    INTERNATIONAL JOURNAL OF STRUCTURAL STABILITY AND DYNAMICS, 2018, 18 (05)
  • [48] The Measurement of Radar-Plasma Signatures in a Hypersonic Shock Tunnel: Simulation and Experiment
    Petervari, Rene
    Weidner, Stephan
    Nekris, Alexander
    Brueggenwirth, Stefan
    Knott, Peter
    IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS, 2023, 59 (06) : 8581 - 8597
  • [49] Shock Tunnel Experiments and CFD Simulation of Lateral Jet Interaction in Hypersonic Flows
    Havermann, M.
    Seiler, F.
    Hennig, P.
    NEW RESULTS IN NUMERICAL AND EXPERIMENTAL FLUID MECHANICS VII, 2010, 112 : 365 - +
  • [50] Gas temperature layer visualization in hypersonic shock tunnel using electric discharge
    Jagadeesh, G
    Nagashetty, K
    Rao, BRS
    Reddy, KPJ
    24TH INTERNATIONAL CONGRESS ON HIGH-SPEED PHOTOGRAPHY AND PHOTONICS, 2001, 4183 : 864 - 871
12345