Investigation was conducted in Langley transonic blowdown tunnel to compare two methods for reducing pressure drag; results indicate that, for relatively slender configuration, streamline concept of shaping fuselage does not offer pressure drag reduction greater than that obtainable with supersonic-area-rule concept.
Effect of streamline contouring in wing-fuselage juncture in combination with supersonic area rule on swept-back-wing-fuselage configuration of high fineness ratio
NASA -- Tech Note
1960
19 pages
Report
English
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