Experimental and theoretical section wave drag coefficients for a 60° delta wing with two airfoil sections are presented for a Mach number of 1.6. One airfoil section was an NACA 65AOO6, and the other was that 6-pereent section which gives a delta wing the longitudinal cross-sectional area distribution of a Sears-Haack optimum body of revolution for a given length and volume.nFor a given airfoil section the experimental chordwise pressure distributions were much the same at every spanwise station. Hence, the results showed only small measured variations of section wave drag coefficient along the span in contrast to the larger variations, predicted by linear theory.nThe experimental spanwise drag loadings were nearly the same foil the two airfoil sections. The 65A wing had about three-fourths of the wave drag coefficient of the Sears-Haack wing. The linear theory did predict the 65A section to be the better section at a Mach number Of 1.6, but made a 17-percent error in the amount of the drag of this section.
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