NDLI: Effect of afterbody-ejector configurations on the performance at transonic speeds of a pylon-supported nacelle model having a hot-jet exhaust

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Effect of afterbody-ejector configurations on the performance at transonic speeds of a pylon-supported nacelle model having a hot-jet exhaust

Content Provider	NASA Technical Reports Server (NTRS)
Copyright Year	1959
Description	An investigation of several afterbody-ejector configurations on a pylon-supported nacelle model has been completed in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05. The propulsive performance of two nacelle afterbodies with low boattailing and long ejector spacing was compared with a configuration corresponding to a turbojet-engine installation having a highly boattailed afterbody with a short ejector. The jet exhaust was simulated with a hydrogen peroxide turbojet simulator. The angle of attack was maintained at 0 deg, and the average Reynolds number based on body length was 20 x 10(exp 6). The results of the investigation indicated that the configuration with a conical afterbody with smooth transition to a 15 deg boattail angle had large beneficial jet effects on afterbody pressure-drag coefficient and had the best thrust-minus-drag performance of the afterbody-ejector configurations investigated.
File Size	2065585
Page Count	56
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19980228466
Archival Resource Key	ark:/13960/t1wd8kt03
Language	English
Publisher Date	1959-02-01
Access Restriction	Open
Subject Keyword	Aerodynamics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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