Boundary-Layer Transition on Cones Near Mach One in an Aeroballistic Range
Final rept. 1 Jul 1973-30 Jun 1974
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
Pagination or Media Count:
The feasibility of determining Reynolds numbers of boundary layer transition on sharp, 10-deg, semiangle cones at slightly supersonic free-stream Mach numbers, 1.04 or M or 1.44, in an aeroballistic range has been demonstrated. Some problems relating to the experimental technique are discussed, and the data are compared with results for higher Mach numbers. Possibly important differences between transonic wind tunnels and the aeroballistic range are pointee out in connection with a warning about comparing transition data from different facilities.
- Ammunition and Explosives
- Fluid Mechanics