A 4 in by 4 in "blow-down" supersonic wind tunnel capable of testing at Mach numbers from 1.5 to 3.5 (see Fig. 8) is used principally for instruction. A schlieren system is used to observe shock waves optically.
Fig. 8 "Blow-down" Supersonic Wind Tunnel.
Fig. 9 Wind Tunnel Model
Coordinator: Anwar Ahmed
aahmed@eng.auburn.edu
(334) 844-6817
