Effect of Afterbody Geometry and Sting Diameter on the Aerodynamic Characteristics of Slender Bodies at Mach Number from 1.57 to 2.86
Author: Dennis E. Fuller
Publisher:
Published: 1963
Total Pages: 38
ISBN-13:
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Author: Dennis E. Fuller
Publisher:
Published: 1963
Total Pages: 38
ISBN-13:
DOWNLOAD EBOOKAuthor: Dennis E. Fuller
Publisher:
Published: 1963
Total Pages: 0
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DOWNLOAD EBOOKAuthor: Linda S. Bangert
Publisher:
Published: 1992
Total Pages: 272
ISBN-13:
DOWNLOAD EBOOKAuthor: Linda S. Bangert
Publisher:
Published: 1991
Total Pages: 224
ISBN-13:
DOWNLOAD EBOOKAuthor: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
Published: 2018-07-24
Total Pages: 272
ISBN-13: 9781723563997
DOWNLOAD EBOOKA parametric study was conducted in the Langley 16-Foot Transonic Tunnel on an isolated nonaxisymmetic fuselage model that simulates a twin-engine fighter. The effects of aft-end closure distribution (top/bottom) nozzle-flap boattail angle versus nozzle-sidewall boattail angle) and afterbody and nozzle corner treatment (sharp or radius) were investigated. Four different closure distributions with three different corner radii were tested. Tests were conducted over a range of Mach numbers from 0.40 to 1.25 and over a range of angles of attack from -3 to 9 degrees. Solid plume simulators were used to simulate the jet exhaust. For a given closure distribution in the range of Mach numbers tested, the sharp-corner nozzles generally had the highest drag, and the 2-in. corner-radius nozzles generally had the lowest drag. The effect of closure distribution on afterbody drag was highly dependent on configuration and flight condition. Bangert, Linda S. and Carson, George T., Jr. Langley Research Center NASA-TP-3236, L-17034, NAS 1.60:3236 RTOP 505-62-30-01...
Author: Wladimiro Calarese
Publisher:
Published: 1978
Total Pages: 184
ISBN-13:
DOWNLOAD EBOOKAn experimental investigation has been performed to determine the effects of boattail injection and jet flow simulation on the afterbody drag of a slender body of revolution in the transonic regime at zero angle of attack, such as engine nacelles and boattailed afterbodies with isolated engines. A correlation between sting and jet diameter has been established. The jet plume and the nozzle pressure ratio simulators have been found appropriate and useful as a testing technique. Boattail mass injection usually produces a drag coefficient reduction and is more effective at high nozzle pressure ratios. Boattail injection is more effective if used in regions of separated flow. (Author).
Author: Dennis E. Fuller
Publisher:
Published: 1963
Total Pages: 40
ISBN-13:
DOWNLOAD EBOOKAuthor: James F. Campbell
Publisher:
Published: 1967
Total Pages: 44
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DOWNLOAD EBOOKAuthor: A. B. Carraway
Publisher:
Published: 1960
Total Pages: 124
ISBN-13:
DOWNLOAD EBOOKAuthor: Ross B. Robinson
Publisher:
Published: 1959
Total Pages: 38
ISBN-13:
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