ordinates-and-theoretical-pressure-distribution-data-for-naca-6-and-6a-series-airfoil-sections-with-thicknesses-from-2-to-21-and-from-2-to-15-percent-chord-respectively--with-list-of-references-

Ordinates And Theoretical Pressure Distribution Data For NACA 6 And 6A Series Airfoil Sections With Thicknesses From 2 To 21 And From 2 To 15 Percent Chord Respectively With List Of References

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