scholarly journals 100 kHz PLEET velocimetry in a Mach-6 Ludwieg tube

2020 ◽  
Vol 28 (15) ◽  
pp. 21982
Author(s):  
Paul S. Hsu ◽  
Naibo Jiang ◽  
Joseph S. Jewell ◽  
Josef J. Felver ◽  
Matthew Borg ◽  
...  
Keyword(s):  
Ludwieg Tube

Film cooling experimental technique using a Ludwieg tube wind tunnel

1993 ◽  
Vol 6 (2) ◽  
pp. 186-195
Author(s):  
Ming-Yuan Zhang ◽  
Fu-Kang Tsou ◽  
Xue-Jun Chen ◽  
Shih-Jiun Chen
Keyword(s):  
Wind Tunnel ◽  
Experimental Technique ◽  
Film Cooling ◽  
Ludwieg Tube

scholarly journals Transitional shock-wave/boundary-layer interactions in hypersonic flow

2014 ◽  
Vol 752 ◽  
pp. 349-382 ◽  
Author(s):  
N. D. Sandham ◽  
E. Schülein ◽  
A. Wagner ◽  
S. Willems ◽  
J. Steelant
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Pressure Sensors ◽  
Transition Process ◽  
Strong Interactions ◽  
Present Contribution ◽  
High Enthalpy ◽  
Reflected Shock ◽  
Ludwieg Tube ◽  
Streamwise Streaks

AbstractStrong interactions of shock waves with boundary layers lead to flow separations and enhanced heat transfer rates. When the approaching boundary layer is hypersonic and transitional the problem is particularly challenging and more reliable data is required in order to assess changes in the flow and the surface heat transfer, and to develop simplified models. The present contribution compares results for transitional interactions on a flat plate at Mach 6 from three different experimental facilities using the same instrumented plate insert. The facilities consist of a Ludwieg tube (RWG), an open-jet wind tunnel (H2K) and a high-enthalpy free-piston-driven reflected shock tunnel (HEG). The experimental measurements include shadowgraph and infrared thermography as well as heat transfer and pressure sensors. Direct numerical simulations (DNS) are carried out to compare with selected experimental flow conditions. The combined approach allows an assessment of the effects of unit Reynolds number, disturbance amplitude, shock impingement location and wall cooling. Measures of intermittency are proposed based on wall heat flux, allowing the peak Stanton number in the reattachment regime to be mapped over a range of intermittency states of the approaching boundary layer, with higher overshoots found for transitional interactions compared with fully turbulent interactions. The transition process is found to develop from second (Mack) mode instabilities superimposed on streamwise streaks.

Numerical rebuilding of the flow in a valve-controlled Ludwieg tube

Shock Waves ◽  
2009 ◽  
pp. 665-670 ◽  
Author(s):  
T. Wolf ◽  
M. Estorf ◽  
R. Radespiel
Keyword(s):  
Ludwieg Tube

Hypersonic Ludwieg Tube

2015 ◽  
pp. 433-458 ◽  
Author(s):  
Rolf Radespiel ◽  
Malte Estorf ◽  
Dirk Heitmann ◽  
Federico Muñoz ◽  
Torsten Wolf
Keyword(s):  
Ludwieg Tube

Nuclear Blast Response of Airbreathing Propulsion Systems: Laboratory Measurements With an Operational J-85-5 Turbojet Engine

1982 ◽  
Vol 104 (3) ◽  
pp. 624-632 ◽  
Author(s):  
M. G. Dunn ◽  
J. M. Rafferty
Keyword(s):  
Frequency Response ◽  
Blast Wave ◽  
Test Section ◽  
Maximum Speed ◽  
Laboratory Measurements ◽  
Propulsion Systems ◽  
Pressure Transducers ◽  
Ludwieg Tube ◽  
Turbojet Engine ◽  
Blast Response

This paper describes an experimental technique that has been developed for the performance of controlled laboratory measurements of the nuclear blast response of airbreathing propulsion systems. The experiments utilize an available G.E. J-85-5 turbojet engine located in the test section of the Calspan Ludwieg-tube facility. Significant modifications, described herein, were made to this facility in order to adapt it to the desired configuration. The J-85 engine had previously been used at Calspan for other purposes and thus came equipped with eight pressure transducers at four axial locations along the compressor section. These transducers have a frequency response on the order of 40 KHz. Pressure histories obtained at several circumferential and axial locations along the compressor are presented for blast-wave equivalent overpressures up to 17.2 kPa (2.5 psi) at corrected engine speeds on the order of 94 percent of maximum speed.

Design and Experimental Construction of a Small-scale Supersonic Ludwieg Tube

2004 ◽  
Vol 2004.2 (0) ◽  
pp. 23-24
Author(s):  
Mitsuhiro NADACHI ◽  
Kazuhide MIZOBATA ◽  
Hiromu SUGIYAMA
Keyword(s):  
Small Scale ◽  
Ludwieg Tube

AFRL Ludwieg Tube Initial Performance

2017 ◽  
Author(s):  
Roger L. Kimmel ◽  
Matthew P. Borg ◽  
Joseph S. Jewell ◽  
KIng-Yiu Lam ◽  
Rodney D. Bowersox ◽  
...  
Keyword(s):  
Ludwieg Tube
Sign in / Sign up

Export Citation Format

Share Document