Effects of certain flow nonuniformities on lift, drag, and pitching moment for a transonic-airplane model investigated at a Mach number of 1.2 in a nozzle of circular cross section

Ritchie, Virgil S
naca-rm-l9e20a
August 31, 1949


No Abstract Available

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1949/naca-rm-l9e20a.pdf