Afterbody/Nozzle Pressure Distributions of a Twin-Tail Twin-Engine Fighter with Axisymmetric Nozzles at Mach Numbers from 0. 6 to 1. 2

Afterbody/Nozzle Pressure Distributions of a Twin-Tail Twin-Engine Fighter with Axisymmetric Nozzles at Mach Numbers from 0. 6 to 1. 2
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
Total Pages: 220
Release: 2018-07-23
Genre:
ISBN: 9781723510533
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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. Wing, David J. Langley Research Center NASA-TP-3509, L-17438, NAS 1.60:3509 RTOP 505-59-30-04...

An Investigation of F-16 Nozzle-afterbody Forces at Transonic Mach Numbers with Emphasis on Support System Interference

An Investigation of F-16 Nozzle-afterbody Forces at Transonic Mach Numbers with Emphasis on Support System Interference
Author: Earl A. Price (Jr.)
Publisher:
Total Pages: 416
Release: 1979
Genre: Aerodynamics, Transonic
ISBN:
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A comprehensive experimental program was conducted to provide nozzle-afterbody data with a minimum interference support system on a 1/9-scale F-16 model and to determine the interference induced on the afterbody-nozzle region by a sting, a wingtip, and a strut model support system. The investigation was conducted over the Mach number range from 0.6 to 1.5 and at angles of attack from 0 to 9 deg. Interference was evaluated by comparison of nozzle-afterboy axial and normal forces obtained from integrating pressure data. The results include parametric studies of the efects of various components of the wingtip support system (i.e., the support blade axial position, wingtip boom diameter, boom spacing, and boom-tip axial location). High-pressure air at ambient temperature was utilized for exhaust plume simulation. The results indicate that a sting support passing through the nozzle with the jet effects simulated by an annular jet appears to offer a minimum interference support system for the type of nozzle-afterbody test described in this report.