Source: https://engineering.purdue.edu/AAE/people/ptProfile?resource_id=1274
Timestamp: 2019-04-20 08:15:56+00:00

Document:
High-speed laminar-turbulent transition is critical for applications including missiles for survivable time-critical strike, hypersonic reconnaissance vehicles, thermal protection for re-entry vehicles, drag reduction on supersonic transports, and flow noise and heat transfer above IR windows on interceptor missiles. Unfortunately, nearly all existing high-speed experimental results are contaminated by facility noise, such as that radiating from the turbulent boundary layers normally present on the test-section walls of supersonic tunnels. Just as at low speeds, reliable experimental progress requires low-turbulence wind tunnels with noise levels comparable to those in flight.
Mechanism-based prediction methods are being developed to reduce the uncertainty in predicting transition on future flight vehicles. Measurements of the instability mechanisms leading to transition are being carried out to support the development and validation of these new methods. However, no single wind tunnel can simultaneously simulate all aspects of transition in flight, including Mach number, Reynolds number, enthalpy, freestream disturbances, surface ablation and so on. Furthermore, although computational advances are critical, all computations require models that must be based on experimental results. Effective progress requires cooperation between theory, computation and experiment, and also between system designers and researchers.
Steven P. Schneider, "Developing Mechanism-Based Methods for Estimating Hypersonic Boundary-Layer Transition in Flight: The Role of Quiet Tunnels", Progress in Aerospace Sciences, v. 72, 2015, pp. 17-29.
Steven P. Schneider, "Hypersonic Boundary-Layer Transition on Blunt Bodies with Roughness," Journal of Spacecraft and Rockets, v. 45, No. 6, Nov.-Dec. 2008, pp. 1090-1105.
Matthew P. Borg and Steven P. Schneider, "Effect of Freestream Noise on Roughness-Induced Transition for the X-51A Forebody," Journal of Spacecraft and Rockets, V. 45, No. 6, Nov.-Dec. 2008, pp. 1106-1116.
Steven P. Schneider, "The Development of Hypersonic Quiet Tunnels," Journal of Spacecraft and Rockets, V. 45, No. 4, July/August 2008, pp. 641-664.
Thomas J. Juliano, Steven P. Schneider, Selin Aradag, and Doyle Knight, "A Quiet-Flow Ludwieg Tube for Hypersonic Transition Research," AIAA Journal, V. 46, No. 7, July 2008, pp. 1757-1763.
Steven P. Schneider, "Effects of Roughness on Hypersonic Boundary Layer Transition," Journal of Spacecraft and Rockets, V. 45, No. 2, March-April 2008, pp. 193-209.
Steven P. Schneider, "Laminar-Turbulent Transition on Reentry Capsules and Planetary Probes," J. of Spacecraft and Rockets, vol. 43, no. 6, Nov.-Dec. 2006, pp. 1153-1173.
Steven P. Schneider, "Hypersonic Laminar-Turbulent Transition on Circular Cones and Scramjet Forebodies," Progress in Aerospace Sciences, 40, no. 1-2, Jan.-Feb. 2004, pp. 1–50.
Steven P. Schneider, "Effects of High-Speed Tunnel Noise on Laminar-Turbulent Transition," J. of Spacecraft and Rockets, vol. 38, no. 3, May-June 2001, pp. 323-333.
Steven P. Schneider, "Flight Data for Boundary-Layer Transition at Hypersonic and Supersonic Speeds," J. of Spacecraft and Rockets, vol. 35, no. 1, Jan.-Feb. 1999, pp. 8-20.
For a current list, see the folder for the Mach-6 tunnel website.

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