Design and Fabrication of a 9.5-inch Mach-6 Quiet-Flow Ludwieg Tube

A high Reynolds-number Mach-6 quiet-flow Ludwieg tube is being developed at Purdue University, based on the existing Mach-4 Ludwieg tube. The design is almost complete and fabrication is about half complete. The 9.5-inch nozzle was designed with e**N methods in order to maintain a laminar nozzle-wall boundary layer, as described earlier. The mechanical design of the nozzle is sketched. In addition, boundary-layer separation should be eliminated in the contraction and driver tube, in order to reduce residual noise that will propagate into the test section via acoustic or convective means. The contraction and bleed-lip design was carried out using the Rott-Crabtree method and an axisymmetric panel-method code. Matched cubics were used for the contraction shape, as suggested by Morel (1975). The detailed design of the driver tube, contraction, and nozzle is described.

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

[2]  J. Schmisseur,et al.  Laser-induced resonance in a forward-facing cavity at Mach 4 , 1997 .

[3]  A. Pope,et al.  High-Speed Wind Tunnel Testing , 1965 .

[4]  R. Kimmel,et al.  Drag Prediction and Transition in Hypersonic Flow , 1997 .

[5]  I. E. Beckwith,et al.  Design and operational features of low-disturbance wind tunnels at NASA Langley for Mach numbers from 3.5 to 18 , 1990 .

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

[7]  I. E. Beckwith,et al.  Supersonic and hypersonic quiet tunnel technology at NASA Langley , 1992 .

[8]  Steven P. Schneider,et al.  A quiet-flow Ludwieg tube for experimental study of high speed boundary layer transition , 1991 .

[9]  S. Wilkinson,et al.  Status of NASA Langley quiet flow facility developments , 1994 .

[10]  John C. Strikwerda,et al.  A Time-Split Difference Scheme for the Compressible Navier–Stokes Equations with Applications to Flows in Slotted Nozzles , 1982 .

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

[12]  James H. Bell,et al.  Contraction Design for Small Low-Speed Wind Tunnels , 1988 .

[13]  Laminar Boundary Layers Developed within Unsteady Expansion and Compression Waves , 1972 .

[14]  Steven P. Schneider,et al.  Effect of Heating on Quiet Flow in a Mach 4 Ludwieg Tube , 1998 .

[15]  von E. Becker,et al.  Instationäre grenzschichten hinter verdichtungsstössen und expansionswellen , 1961 .

[16]  P. Stephen,et al.  A Review of Hypersonic Boundary Layer Stability Experiments in a Quiet Mach 6 Wind Tunnel , 1997 .

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

[18]  Jan Łukasiewicz,et al.  Experimental methods of hypersonics , 1973 .

[19]  Roddam Narasimha,et al.  Relaminarization of fluid flows , 1979 .

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

[21]  R. I. Starr,et al.  Experimental Studies of a Ludwieg Tube High Reynolds Number Transonic Tunnel , 1973 .

[22]  I. E. Beckwith,et al.  Fluctuating disturbances in a Mach 5 wind tunnel , 1977 .

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

[24]  D. A. Russell,et al.  Viscous Effects in Tube Flow Initiated by an Expansion Wave , 1977 .

[25]  J. L. Hess,et al.  Improved solution for potential flow about arbitrary axisymmetric bodies by the use of a higher-order surface source method. Part 1. Theory and results. [the parobolic-element linear source method] , 1974 .

[26]  Steven P. Schneider,et al.  Development of square nozzles for supersonic low-disturbance wind tunnels , 1996 .

[27]  Thomas Morel,et al.  Comprehensive Design of Axisymmetric Wind Tunnel Contractions , 1975 .

[28]  J. Hess,et al.  Calculation of potential flow about arbitrary bodies , 1967 .

[29]  F. White Viscous Fluid Flow , 1974 .

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

[31]  Steven P. Schneider,et al.  Use of Laser Differential Interferometry to Study Receptivity on a Hemispherical Nose at Mach 4 , 1998 .

[32]  Eckart Piltz Boundary-Layer Effects on Pressure Variations in Ludwieg Tubes , 1972 .

[33]  Steven Philip Schneider Effects of controlled three-dimensional perturbations on boundary layer transition , 1989 .