Low-disturbance or 'quiet' wind tunnels are now considered an essential part of meaningful boundary layer transition research. Advances in Supersonic Laminar Flow Control (SLFC) technology for swept wings depends on a better understanding of the receptivity of the transition phenomena to attachment-line contamination and cross-flows. This need has provided the impetus for building the Laminar Flow Supersonic Wind Tunnel (LFSWT) at NASA-Ames, as part of the NASA High Speed Research Program (HSRP). The LFSWT was designed to provide NASA with an unequaled capability for transition research at low supersonic Mach numbers (<2.5). The following are the objectives in support of the new Fluid Mechanic Laboratory (FML) quiet supersonic wind tunnel: (I) Develop a unique injector drive system using the existing FML indraft compressor; (2) Develop an FML instrumentation capability for quiet supersonic wind tunnel evaluation and transition studies at NASA-Ames; (3) Determine the State of the Art in quiet supersonic wind tunnel design; (4) Build and commission the LFSWT; (5) Make detailed flow quality measurements in the LFSWT; (6) Perform tests of swept wing models in the LFSWT in support of the NASA HSR program; and (7) Provide documentation of research progress.
Development of a Quiet Supersonic Wind Tunnel with a Cryogenic Adaptive Nozzle
1995
97 pages
Report
Keine Angabe
Englisch
Test Facilities & Equipment , Aerodynamics , Boundary layer transition , Cryogenics , Flow distribution , Flow measurement , Laminar flow , Nozzle design , Supersonic flow , Supersonic nozzles , Supersonic wind tunnelsab , Swept wings , Wind tunnel apparatus , Cross flow , Injectors , Mach number , Measuring instrumentse , Schlieren photography , Wall flow , Wind tunnel walls