A high Reynolds number wind tunnel test was conducted to assess Reynolds number effects on the aerodynamic performance characteristics of a realistic, second-generation supersonic transport concept. The tests included longitudinal studies at transonic and low-speed, high-lift conditions across a range of chord Reynolds numbers (8 million to 120 million). Results presented focus on Reynolds number and static aeroelastic sensitivities at Mach 0.30 and 0.90 for a configuration without a tail. Static aeroelastic effects, which mask Reynolds number effects, were observed. Reynolds number effects were generally small and the drag data followed established trends of skin friction as a function of Reynolds number. A more nose-down pitching moment was produced as Reynolds number increased because of an outward movement of the inboard leading-edge separation at constant angles of attack. This study extends the existing Reynolds number database for supersonic transports operating at off-design conditions.


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    Title :

    Off-Design Reynolds Number Effects for a Supersonic Transport


    Contributors:

    Publication date :

    2005-01-01


    Type of media :

    Preprint


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Off-Design Reynolds Number Effects for a Supersonic Transport

    L. R. Owens / R. A. Wahls / S. M. Rivers | NTIS | 2005



    Off-Design Reynolds Number Effects for a Supersonic Transport

    Lewis Owens / Richard Wahls / S. Melissa Rivers | AIAA | 2005


    Reynolds Number Effects on a Supersonic Transport at Transonic Conditions

    Wahls, R. N. / Owens, L. R. / Rivers, S. M. B. | NTRS | 2001