## NACA technical note, Volumes 3706-3721 |

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aerodynamic AERONAUTICS TECHNICAL NOTE airfoil angle of attack approximately assumed axial base body of revolution boundary layer calculated characteristics circular cylinder comparison cone-cylinder configuration constant cross-section area curve density diameter downwash drag coefficient equation expansion wave experimental fineness ratio fluctuations fluid flutter frontal area function Guide-vane turning angle heat exchanger heat transfer heat-transfer hot-wire hydraulic diameter inch inclined body increase indicated integral investigation laminar Langley linear Mach number measured method NACA NACA TN normal-force nose nozzle obtained orifice parameter pitot plane predicted pressure coefficient pressure distributions probe reference relation Reynolds number rotating stall rotor scattering shock waves shown in figure sketch slender bodies slender-body theory solution sonic flow speed stagnation point stall zones station stators supersonic surface tanks tests theoretical theory thickness tion transonic tunnel turbulent boundary layer values velocity vortex vortices wall wave drag X-ray zero