An Experimental Investigation of Forward-Swept Wings at Low Reynolds Numbers 931370
The aerodynamic properties of a forward-swept wing were tested at low Reynolds numbers. The investigation was performed in a low-speed wind tunnel using a reflection plane model. Tunnel balance, model pressure taps, and flow visualization results were utilized to characterize the wing behavior over a range of Reynolds numbers from 0.25 × 106 - 0.75 × 106. In addition, the experimental data is compared to results obtained using a recently developed computer program known as WING3D. This modified Non-Planar Vortex Lattice Method program can calculate total wing lift and surface pressure distributions.
The forward-swept wing has good aerodynamic qualities; in addition, the flow, on the outboard sections of the wing, remains attached beyond stall. The comparison of WING3D and experimental surface pressure distributions is good. The investigation results add to the experimental data base for forward-swept wings at low Reynolds numbers, assist in the evaluation of analysis/design tools, and can be used for low Reynolds number unmanned air vehicle applications.
Citation: Randle, S. and Miller, L., "An Experimental Investigation of Forward-Swept Wings at Low Reynolds Numbers," SAE Technical Paper 931370, 1993, https://doi.org/10.4271/931370. Download Citation
Author(s):
Scott A. Randle, L. Scott Miller
Affiliated:
Wichita State Univ.
Pages: 12
Event:
Aerospace Atlantic Conference & Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Related Topics:
Wings
Wind tunnel tests
Imaging and visualization
Stall
Pressure
Aerodynamics
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