Experiment of a Shockless Transonic Airfoil Partially Modified from an Arbitrary Airfoil

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概要

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• An experiment is carried out on a transonic flow over an airfoil, which ispartially modified from an arbitrary airfoil. The modification is made to satisfythe shockless condition predicted by the same author [Jour. Japan Soc. Aero.Space Sci. 26 ([978) [914. Static pressures are measured at 88 points on the airfoilsurface, when the Mach number at wind tunnel wall is 0.5 -0.8, the measuringangle of attack is 0' -4' and the Reynolds number is 4.0 -4.6x lO'. A shocklesstransonic flow is observed under a measuring condition close to the design condi-tion. The supersonic region extends from 0.4 '% to 63 '3 of airfoil chord lengthand the local maximum Mach number is 1.36. The results support that shocklessairfoils can be designed by partial modifications of an arbitrary airfoil.

• 社団法人日本物理学会の論文
• 1982-12-15

著者

• Nakamura Masayoshi

  Division Of Aerodynamics National Aerospace Laboratory

関連論文

• Experiment of a Shockless Transonic Airfoil Partially Modified from an Arbitrary Airfoil

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