文档介绍：AIAA-2001-0912
Reynolds Number Effects on a Supersonic
Transport at Transonic Conditions (Invited)
R. A. Wahls, L. R. Owens, and S. M. B. Rivers
NASA Langley Research Center
Hampton, Virginia
39th AIAA Aerospace Sciences Meeting & Exhibit
8-11 January 2001
Reno, Nevada
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AIAA-2001-0912
REYNOLDS NUMBER EFFECTS ON A
SUPERSONIC TRANSPORT AT TRANSONIC CONDITIONS
R. A. Wahls*, L. R. Owens†, and S. M. B. Rivers‡
Aerodynamics, Aerothermodynamics, and petency
NASA Langley Research Center
Hampton, Virginia
ABSTRACT experiences, and suggested approaches to
A High Speed Civil Transport configuration ground to flight scaling have been documented
was tested in the National Transonic Facility at the extensively over the years for a variety of vehicle
NASA Langley Research Center as part of NASA’s classes (refs. 1, 2, among many others). Reynolds
High Speed Research Program. The primary number effects are foremost among many factors
purposes of the tests were to assess Reynolds affecting essful ground to flight scaling (refs. 3
number scale effects and the high Reynolds - 5). The Reynolds number is the ratio of inertial to
number aerodynamic characteristics of a realistic, viscous forces, and is the primary aerodynamic
second generation supersonic transport while scaling parameter used to relate sub-scale wind
providing data for the assessment of tunnel models to full-scale aircraft in flight. The
computational methods. The tests included challenge of Reynolds number scaling increases
longitudinal and lateral/directional studies at low- with the size of a full-scale aircraft as the Reynolds
speed high-lift and transonic conditions across a number increment between that obtainable in
range of Reynolds numbers from that available in conventional wind tunnels and flight