A High Speed Civil Transport configuration was tested in the National Transonic Facility at the NASA Langley Research Center as part of NASA's High Speed Research Program. The primary purposes of the tests were to assess Reynolds number scale effects and the high Reynolds number aerodynamic characteristics of a realistic, second generation supersonic transport while providing data for the assessment of computational methods. The tests included longitudinal and lateral/directional studies at low speed high-lift and transonic conditions across a range of Reynolds numbers from that available in conventional wind tunnels to near flight conditions. Results are presented which focus on both the Reynolds number and static aeroelastic sensitivities of longitudinal characteristics at Mach 0.90 for a configuration without an empennage.
Reynolds Number Effects on a Supersonic Transport at Transonic Conditions
Aerospace Sciences ; 2001 ; Reno, NV, United States
2001-01-01
Preprint
No indication
English
Reynolds Number Effects on a Supersonic Transport at Transonic Conditions (Invited)
British Library Conference Proceedings | 2001
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