An experimental investigation of hypersonic flow over blunt nosed cones at a mach number of 5.8
Six spherical nosed cone static pressure models with cone semivertex angles of 10°, 20°, and 40° were tested in the GALCIT 5 x 5 inch hypersonic wind tunnel at a Mach number of 5.8. The static pressure distributions obtained at yaw angles of 0°, 4°, and 8° agreed very closely with the modified Newto...
Internet
https://thesis.library.caltech.edu/1135/3/Machell_rm_1956.pdfMachell, Reginald M. (1956) An experimental investigation of hypersonic flow over blunt nosed cones at a mach number of 5.8. Engineer's thesis, California Institute of Technology. doi:10.7907/SJ75-6W93. https://resolver.caltech.edu/CaltechETD:etd-03262004-145512 <https://resolver.caltech.edu/CaltechETD:etd-03262004-145512>