NDLI: Effect of a rotating propeller on the separation angle of attack and distortion in ducted propeller inlets

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Effect of a rotating propeller on the separation angle of attack and distortion in ducted propeller inlets

Content Provider	NASA Technical Reports Server (NTRS)
Author	Boldman, D. R. Larkin, M. Iek, C. Schweiger, P. Hwang, D. P.
Copyright Year	1993
Description	The present study represents an extension of an earlier wind tunnel experiment performed with the P&W 17-in. Advanced Ducted Propeller (ADP) Simulator operating at Mach 0.2. In order to study the effects of a rotating propeller on the inlet flow, data were obtained in the UTRC 10- by 15-Foot Large Subsonic Wind Tunnel with the same hardware and instrumentation, but with the propeller removed. These new tests were performed over a range of flow rates which duplicated flow rates in the powered simulator program. The flow through the inlet was provided by a remotely located vacuum source. A comparison of the results of this flow-through study with the previous data from the powered simulator indicated that in the conventional inlet the propeller produced an increase in the separation angle of attack between 4.0 deg at a specific flow of 22.4 lb/sec-sq ft to 2.7 deg at a higher specific flow of 33.8 lb/sec-sq ft. A similar effect on separation angle of attack was obtained by using stationary blockage rather than a propeller.
File Size	7865087
Page Count	17
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19930007436
Archival Resource Key	ark:/13960/t5dc2zc3d
Language	English
Publisher Date	1993-01-01
Access Restriction	Open
Subject Keyword	Aerodynamics Subsonic Wind Tunnels Vacuum Subsonic Speed Shrouded Propellers Wind Tunnel Tests Flow Velocity Inlet Flow Angle of Attack Separated Flow Rotation Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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