NASA Technical Reports Server (NTRS) : Afterbody/nozzle pdf

NASA Technical Reports Server (NTRS) : Afterbody/nozzle

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Distributions of static pressure coefficient over the afterbody and axisymmetric nozzles of a generic, twin-tail twin-engine fighter were obtained in the Langley 16-Foot Transonic Tunnel. The longitudinal positions of the vertical and horizontal tails were varied for a total of six aft-end configurations. Static pressure coefficients were obtained at Mach numbers between 0.6 and 1.2, angles of attack between 0 deg and 8 deg, and nozzle pressure ratios ranging from jet-off to 8. The results of this investigation indicate that the influence of the vertical and horizontal tails extends beyond the vicinity of the tail-afterbody juncture. The pressure distribution affecting the aft-end drag is influenced more by the position of the vertical tails than by the position of the horizontal tails. Transonic tail-interference effects are seen at lower free-stream Mach numbers at positive angles of attack than at an angle of attack of 0 deg

• Creator/s: NASA Technical Reports Server (NTRS
• Date: 5/1/1995
• Year: 1995
• Book Topics/Themes: NASA Technical Reports Server (NTRS), AERODYNAMIC CONFIGURATIONS, AFTERBODIES, PRESSURE DISTRIBUTION, STATIC PRESSURE, TAIL ASSEMBLIES, TRANSONIC SPEED, WIND TUNNEL TESTS, AERODYNAMIC DRAG, ANGLE OF ATTACK, FIGHTER AIRCRAFT, FREE FLOW, MACH NUMBER, NAVIER-STOKES EQUATION, PRESSURE RATIO, Wing, David J

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