Uncertainty of Aerodynamic Coefficients at Hypersonic Wind Tunnels
نویسندگان
چکیده
منابع مشابه
Development of Hypersonic Quiet Tunnels
a = speed of sound e = integrated amplification ratio for a linear instability, usually from location of first instability to transition k = roughness height Mw = Mach number at the nozzle wall, at the boundarylayer edge M1 = Mach number in the freestream N factor = ln A=A0, the linear-theory amplification ratio from onset of instability A0 usually to measured transition A Pmean = mean pitot pr...
متن کامل1 X - 33 Hypersonic Aerodynamic Characteristics
Lockheed Martin Skunk Works, under a cooperative agreement with NASA, will build and fly the X-33, a half-scale prototype of a rocket-based, single-stage-to-orbit (SSTO), reusable launch vehicle (RLV). A 0.007-scale model of the X-33 604B0002G configuration was tested in four hypersonic facilities at the NASA Langley Research Center to examine vehicle stability and control characteristics and t...
متن کاملParallel Computation in Hypersonic Aerodynamic Heating Problem
A parallel computational fluid dynamics code has been developed for the study of aerodynamic heating problem in hypersonic flows. The code employs the 3D Navier-Stokes equations as the basic governing equations to simulate the laminar hypersonic flow. The cell centered finite volume method based on structured grid is applied for spatial discretization. The AUSMPW+ scheme is used for the invisci...
متن کاملDigital holographic interferometry at F4-ONERA hypersonic wind tunnel
The feasibility of digital holographic interferometry using a CW laser @ 532 nm and a Photron APX camera is demonstrated in the F4-ONERA hypersonic wind tunnel. This optical technique is used to point out the possible combustion of a small hydrogen jet in the shock layer developed on the model. The optical technique generates in the field under analysis, interference micro-fringes which are use...
متن کاملFlow Visualization in Wind Tunnels
Flow visualization is an experimental means of examining the flow patterns around a body or over its surface. The flow is “visualized” by introducing dye, smoke or pigment into the flow in the area under investigation. The primary advantage of such a method is its ability to provide a description of the flow over a model without a complicated data reduction and analysis. Smokeflow visualization...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
سال: 2003
ISSN: 1344-6460
DOI: 10.2322/jjsass.51.151