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Wind tunnel tests of a 20 inch diameter 1.15 pressure ratio fan engine model

Author
Wesoky, H. L.
Published
JAN 1, 1973.
Physical Description
1 electronic document
Additional Creators
Steffen, F. W.
Online Version

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Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
Aerodynamic and acoustic measurements at a typical STOL aircraft takeoff and landing velocity demonstrated that a 1.35 inlet lip area contraction ratio was superior to a 1.26 ratio at high nacelle incidence angles. Reverse thrust, obtained with a variable pitch rotor, was lower at the landing velocity, and the noise level higher, than at the static condition. High speed tests showed that, for the design cruise Mach number of 0.75, internal losses and external drag were 27 percent of the ideal fan net thrust, and propulsive efficiency was estimated to be 59 percent for an 85 percent efficient fan stage.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19730023199.
Accession ID: 73N31931.
NASA-TM-X-71445.
E-7705.
Propulsion Joint Specialist Conf.; 5-7 Nov. 1973; Las Vegas, NV; United States.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15747605