An Experimental Investigation of Separated Flow on a Light Twin Engine Aircraft 830772
Force measurements, surface flow patterns and wake total pressure surveys have been obtained for a wing, wing--body, wing-nacelle and wing-body--nacelle configuration at typical pre-and post-stall angle of attack (10° and 16°), for a general aviation twin-engine airplane. The data includes separated regions and combined flow field models.
The results indicate the presence of highly three-dimensional separated regions above and beyond the surface at post-stall condition.
Based upon the present experimental data, combined flow field models have been proposed for each of the configurations, at the pre-stall (10°) and post -stall (16°) angle of attack condition. In all cases, the flow is shown to be forming turbulent three-dimensional separation bubbles. These flow models should provide some guidelines for future analytical modeling of separated flow associted with interfering bodies.
Citation: Ostowari, C. and Wentz, W., "An Experimental Investigation of Separated Flow on a Light Twin Engine Aircraft," SAE Technical Paper 830772, 1983, https://doi.org/10.4271/830772. Download Citation
Author(s):
C Ostowari, W. H. Wentz
Affiliated:
Texas A & M University, Wichita State University
Pages: 16
Event:
Business Aircraft Meeting and Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
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