A PRELIMINARY INVESTIGATION TO STUDY THE EFFECT OF FLAT SPOILERS ON THE AERODYNAMIC CHARACTERISTICS OF WINGS AT ANGLES OF ATTACK FROM 0 DEGREES TO 90 DEGREES.
Research and development rept.
DAVID TAYLOR MODEL BASIN WASHINGTON D C AERODYNAMICS LAB
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Flat spoilers were tested on a semispan wing as a possible leading-edge, upper-surface device for controlling flow separation on wings rotated through 90 degrees for application to tilt-wing VSTOL aircraft. Model tests indicated that a spoiler height of 0.10 wing chord at the 0.15 wing chord location was capable of partially controlling flow separation. Author
- Fluid Mechanics