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In-flight flow visualization results from the X-29A aircraft at high angles of attackFlow visualization techniques were used on the X-29A aircraft at high angles of attack to study the vortical flow off the forebody and the surface flow on the wing and tail. The forebody vortex system was studied because asymmetries in the vortex system were suspected of inducing uncommanded yawing moments at zero sideslip. Smoke enabled visualization of the vortex system and correlation of its orientation with flight yawing moment data. Good agreement was found between vortex system asymmetries and the occurrence of yawing moments. Surface flow on the forward-swept wing of the X-29A was studied using tufts and flow cones. As angle of attack increased, separated flow initiated at the root and spread outboard encompassing the full wing by 30 deg angle of attack. In general, the progression of the separated flow correlated well with subscale model lift data. Surface flow on the vertical tail was also studied using tufts and flow cones. As angle of attack increased, separated flow initiated at the root and spread upward. The area of separated flow on the vertical tail at angles of attack greater than 20 deg correlated well with the marked decrease in aircraft directional stability.
Document ID
19930004134
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Delfrate, John H. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Saltzman, John A. (PRC Kentron, Inc. Edwards, CA., United States)
Date Acquired
September 6, 2013
Publication Date
November 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-4102
NAS 1.15:4430
NASA-TM-4430
H-1825
Meeting Information
Meeting: Biennial Flight Test Conference
Location: Hilton Head, SC
Country: United States
Start Date: August 24, 1992
End Date: August 26, 1992
Accession Number
93N13322
Funding Number(s)
PROJECT: RTOP 533-02-38
Distribution Limits
Public
Copyright
Public Use Permitted.

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