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Large-scale Flight Measurements of Zero-lift Drag at Mach Numbers Form 0.86 to 1.5 of a Wing-body Combination Having a 60 Degree Triangular Wing with NACA 65A003 Sections

Robert L. Nelson

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Abstract

Report presenting flight testing at high-subsonic and supersonic speeds at high Reynolds numbers to determine the zero-lift drag of a fin-stabilized body and a wing-body combination. The body was parabolic in profile, had a fineness ratio of 10, and a ratio of body frontal area to wing area to 0.306.

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Report presenting flight testing at high-subsonic and supersonic speeds at high Reynolds numbers to determine the zero-lift drag of a fin-stabilized body and a wing-body combination. The body was parabolic in profile, had a fineness ratio of 10, and a ratio of body frontal area to wing area to 0.306.

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Available abstract

Report presenting flight testing at high-subsonic and supersonic speeds at high Reynolds numbers to determine the zero-lift drag of a fin-stabilized body and a wing-body combination. The body was parabolic in profile, had a fineness ratio of 10, and a ratio of body frontal area to wing area to 0.306.

Key concepts: Wing, Wing twist, Lift-to-drag ratio, Vortex lift, Angle of attack, Drag, Lift (data mining), Reynolds number

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Large-scale Flight Measurements of Zero-lift Drag at Mach Numbers Form 0.86 to 1.5 of a Wing-body Combination Having a 60 Degree Triangular Wing with NACA 65A003 Sections — Research Paper | ScholarLens