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Aerodynamic characteristics of a jet sheet vortex generatorA configuration concept for augmenting the lift capability of low aspect ratio, thin wings, typically used on fighter aircraft was investigated. The fluid strake concept uses a jet sheet formed by blowing from a series of small orifices located in the side of the fuselage ahead of the wing to generate a stable vortex flow over the wing at high angle of attack. The effect of the location of the fluid strake relative to the wing was investigated for three different designs of the in-line orifices using a half-span model tested in a 7 by 10 foot low speed tunnel. Based on the results of the low speed test, a jet sheet producing module was incorporated into a NASA general research fighter model and tested in the Langley 7 by 10 foot high speed tunnel to determine the effectiveness of the fluid strake as a lift-enhancement device in the high-speed maneuver regime. Tests were conducted over a Mach number range from 0.3 to 0.8, with a jet momentum coefficient range from 0 to 0.24. Significant lift increments resulted at the higher angles of attack and drag polars were improved.
Document ID
19780020111
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Ziegler, H. (Northrop Corp. Hawthorne, CA, United States)
Wooler, P. T. (Northrop Corp. Hawthorne, CA, United States)
Date Acquired
September 3, 2013
Publication Date
June 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
NOR-78-24
NASA-CR-158904
Accession Number
78N28054
Funding Number(s)
CONTRACT_GRANT: NAS1-14216
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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