NDLI: Augmentation of maneuver performance by spanwise blowing

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Augmentation of maneuver performance by spanwise blowing

Content Provider	NASA Technical Reports Server (NTRS)
Author	Erickson, G. E. Campbell, J. F.
Copyright Year	1977
Description	A generalized wind tunnel model was tested to investigate new component concepts utilizing spanwise blowing to provide improved maneuver characteristics for advanced fighter aircraft. Primary emphasis was placed on high angle of attack performance, stability, and control at subsonic speeds. Spanwise blowing on a 44 deg swept trapezoidal wing resulted in leading edge vortex enhancement with subsequent large vortex-induced lift increments and drag polar improvements at the higher angles of attack. Small deflections of a leading edge flap delayed these lift and drag benefits to higher angles of attack. In addition, blowing was more effective at higher Mach numbers. Spanwise blowing in conjunction with a deflected trailing edge flap resulted in lift and drag benefits that exceeded the summation of the effects of each high lift device acting alone. Asymmetric blowing was an effective lateral control device at the higher angles of attack. Spanwise blowing on the wing reduced horizontal tail loading and improved the lateral-directional stability characteristics of a wing-horizontal tail-vertical tail configuration.
File Size	9379968
Page Count	244
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19770009040
Archival Resource Key	ark:/13960/t6h17t635
Language	English
Publisher Date	1977-01-01
Access Restriction	Open
Subject Keyword	Aerodynamics Aerodynamic Drag Aircraft Stability Aircraft Maneuvers Wind Tunnel Models Spanwise Blowing Angle of Attack Fighter Aircraft Lift Aircraft Control 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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