Shakedown of the Purdue Mach-6 Quiet-Flow Ludwieg Tube

Purdue University continues to develop a 9.5-inch Mach-6 Ludwieg tube for quiet-flow operation to high Reynolds number. The aerodynamic and mechanical design were reported earlier, along with the design and testing of several facility subsystems. Measurements of the coordinates of the completed upstream nozzle sections are here reported. The development and further testing of other facility systems are also described: these include the second round of burst-diaphragm tests, the bleed-slot suction system, and the driver-tube and contraction heating systems. Delivery of the quiet-flow nozzle is presently scheduled for February 2001. Progress in developing repeatable hot-wire calibrations is also reported.

[1]  Steven P. Schneider,et al.  Mean Flow and Noise Measurements In the Purdue Mach-6 Quiet-Flow , 2001 .

[2]  Steven P. Schneider,et al.  Effects of High-Speed Tunnel Noise on Laminar-Turbulent Transition , 2000 .

[3]  Steven Schneider.  Initial shakedown of the Purdue Mach-6 quiet-flow Ludwieg tube , 2000 .

[4]  M. V. Morkovin.  Probe Interference in Measurements in Supersonic Laminar Boundary Layers , 1954 .

[5]  K. Hannemann.  Numerical Flow Field Analyses of the RWG Mach 6.8 Contoured Nozzle , 1996 .

[6]  S. Schneider.  Design of a Mach-6 Quiet-Flow Wind-Tunnel Nozzle using the e**N Method for Transition Estimation , 1998 .

[7]  D. Rubenstein,et al.  Introduction to heat transfer , 2022 .

[8]  M. Holden,et al.  Ground test facilities for aerothermal and aero-optical evaluation of hypersonic interceptors , 1992 .

[9]  I. E. Beckwith,et al.  Aerothermodynamics and Transition in High-Speed Wind Tunnels at NASA Langley , 1990 .

[10]  J. Laufer,et al.  Measurements of heat transfer from fine wires in supersonic flows , 1956, Journal of Fluid Mechanics.

[11]  Alexander J. Smits,et al.  Constant-temperature hot-wire anemometer practice in supersonic flows. II - The inclined wire , 1983 .

[12]  A. A. Sidorenko,et al.  Experimental investigations of disturbance development in the hypersonic boundary layer on a Conical Model , 2000 .

[13]  I. E. Beckwith,et al.  Boundary-layer transition on a cone and flat plate at Mach 3.5 , 1989 .

[14]  T. Salyer,et al.  Laser differential interferometry for supersonic blunt body receptivity experiments , 2000 .

[15]  C. Forbes Dewey,et al.  Hot-wire Measurements in Low Reynolds Number Hypersonic Flows , 1961 .

[16]  D. K. Mclaughlin,et al.  Supersonic hot-wire fluctuation data analysis with a conduction end-loss correction , 1978 .

[17]  Steven P. Schneider,et al.  Receptivity of the Mach-4 boundary layer on an elliptic cone to laser-generated localized freestream perturbations , 1998 .

[18]  D. Ladoon,et al.  Measurements of controlled wave packets at Mach 4 on a cone at angle of attack , 1998 .

[19]  S. Wagner,et al.  The shock wind tunnel of Stuttgart University - A facility for testing hypersonic vehicles , 1999 .

[20]  S. Schneider,et al.  Fabrication and testing of the Purdue Mach-6 quiet-flow Ludwieg tube , 2000 .

[21]  Steven P. Schneider,et al.  Laser-Generated Localized Freestream Perturbations in Supersonic and Hypersonic Flows , 2000 .

[22]  Stephen P. Wilkinson,et al.  NASA Langley Mach 6 quiet wind-tunnel performance , 1997 .

[23]  Scott E. Munro,et al.  Laminar-turbulent transition research in the Purdue Mach-4 Quiet-Flow Ludwieg Tube , 1996 .

[24]  Y. Jaluria,et al.  An Introduction to Heat Transfer , 1950 .

[25]  I. E. Beckwith,et al.  Free stream noise and transition measurements in a Mach 3.5 pilot quiet tunnel , 1983 .

[26]  John D. Schmisseur.  Receptivity of the boundary layer on a Mach-4 elliptic cone to laser-generated localized freestream perturbations , 1997 .

[27]  Steven P. Schneider,et al.  Design and Fabrication of a 9.5-inch Mach-6 Quiet-Flow Ludwieg Tube , 1998 .

[28]  Steven P. Schneider.  Laminar-flow design for a Mach-6 quiet-flow wind tunnel nozzle , 2000 .

[29]  S. Schneider.  Flight Data for Boundary-Layer Transition at Hypersonic and Supersonic Speeds , 1999 .

[30]  S. Schneider,et al.  Review of optical diagnostic methods for hypersonic low-noise facilities , 1996 .

[31]  Scott A. Berry,et al.  X-33 Hypersonic Boundary Layer Transition , 1999 .

[32]  Dale William Ladoon.  Wave packets generated by a surface glow discharge on a cone at Mach 4 , 1998 .

[33]  W. R. Grabowsky,et al.  The search for optimum configurations for re-entry vehicles , 1984 .

[34]  S. Schneider,et al.  Quiet-flow Ludwieg tube for high-speed transition research , 1995 .

[35]  James M. Kendall,et al.  An Experimental Investigation of Leading-Edge Shock-Wave - Boundary-Layer Interaction at Mach 5.8 , 1957 .

[36]  L. Kovasznay,et al.  The Hot-Wire Anemometer in Supersonic Flow , 1950 .