In early 1996, the ability to run NASA Lewis Research Center's Abe Silverstein 10- by 10- Foot Supersonic Wind Tunnel (10x10) at subsonic test section speeds was reestablished. Taking advantage of this new speed range, a subsonic research test program was scheduled for the 10x10 in the fall of 1996. However, many subsonic aircraft test models require an exhaust source to simulate main engine flow, engine bleed flows, and other phenomena. This was also true of the proposed test model, but at the time the 10x10 did not have a model exhaust capability. So, through an in-house effort over a period of only 5 months, a new model exhaust system was designed, installed, checked out, and made ready in time to support the scheduled test program.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    New Model Exhaust System Supports Testing in NASA Lewis' 10- by 10-Foot Supersonic Wind Tunnel


    Contributors:


    Publication date :

    1998-04-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English





    Flow Quality and Operational Enhancements in the NASA Lewis 8-by 6-Foot Supersonic Wind Tunnel

    Arrington, E. A. / Gonsalez, J. C. / Becks, E. A. et al. | British Library Conference Proceedings | 1998




    AERODYNAMIC TESTING CAPABILITIES OF THE NASA GLENN 10- BY 10-FOOT SUPERSONIC WIND TUNNEL

    Arrington, A. / Pastor, C. / Simerly, S. et al. | British Library Conference Proceedings | 2011