Wind tunnel experiments were conducted to determine the effectiveness of spoilers applied to a finite-span wing which utilizes the GA(W)-1 airfoil section and a 30% chord full-span Fowler flap. A series of spoiler cross sectioned shapes were tested utilizing a reflection-plane model. Five-component force characteristics and hinge moment measurements were obtained. Results confirm earlier two-dimensional tests which showed that spoilers could provide large lift increments at any flap setting, and that spoiler control reversal tendencies could be eliminated by providing a vent path from lower surface to upper surface. Performance penalties due to spoiler leakage airflow were measured.
Reflection-plane tests of spoilers on an advanced technology wing with a large Fowler flap
1976-07-01
Report
Keine Angabe
Englisch
Reflection-Plane Tests of Spoilers on an Advanced Technology Wing
SAE Technical Papers | 1976
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