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Free-flight Investigation at Mach Numbers from 0.8 to 1.5 of the Effect of a Fuselage Indentation on the Zero-lift Drag of a 52.5 Degree Sweptback-wing--body Configuration with Symmetrically Mounted Stores on the Fuselage

Sherwood Hoffman

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Key concepts: Fuselage, Wing, Angle of attack, Drag, Mach number, Lift-to-drag ratio, Degree (music), Vortex lift

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Free-flight Investigation at Mach Numbers from 0.8 to 1.5 of the Effect of a Fuselage Indentation on the Zero-lift Drag of a 52.5 Degree Sweptback-wing--body Configuration with Symmetrically Mounted Stores on the Fuselage — Research Paper | ScholarLens