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| Title: |
A water tunnel flow visualization study of the vortex flow structures on the F/A-18 aircraft
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| Author(s): |
Sandlin, Doral R.; Ramirez, Edgar J.
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| Abstract: |
The vortex flow structures occurring on the F/A-18 aircraft at high angles of attack were studied. A water tunnel was used to gather flow visualization data on the forebody vortex and the wing leading edge extension vortex. The longitudinal location of breakdown of the leading edge vortex was found to be consistently dependent on the angle of attack. Other parameters such as Reynolds number, model scale, and model fidelity had little influence on the overall behavior of the flow structures studied. The lateral location of the forebody vortex system was greatly influenced by changes in the angle of sideslip. Strong interactions can occur between the leading edge extension vortex and the forebody vortex. Close attention was paid to vortex induced flows on various airframe components of the F/A-18. Reynolds number and angle of attack greatly affected the swirling intensity, and therefore the strength of the studied vortices. Water tunnel results on the F/A-18 correlated well with those obtained in similar studies at both full and sub scale levels. The water tunnel can provide, under certain conditions, good simulations of realistic flows in full scale configurations.
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| NASA Center: |
NASA (non Center Specific)
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| Publication Date: |
Jul 1, 1991
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| Document Source: |
CASI |
| Online Source: |
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| Document ID: |
19910017812
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| Accession ID: |
91N27126
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| Publication Information: |
Number of Pages = 124 |
| Report Number: |
NAS 1.26:186938; NASA-CR-186938
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| Contract-Grant-Task Number: |
NCC2-620 |
| Price Code: |
A06 |
| Keywords: |
FLOW DISTRIBUTION; FLOW VISUALIZATION; HYDRAULIC TEST TUNNELS; LEADING EDGES; VORTICES; WING PROFILES; AIRFRAMES; ANGLE OF ATTACK; FOREBODIES; REYNOLDS NUMBER; SCALE MODELS; SIDESLIP; SWIRLING;
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| Accessibility: |
Unclassified; No Copyright; Unlimited; Publicly available; Final Report |
| Updated/Added to NTRS: |
2005-08-25 |
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