Abstract
An experimental investigation of an airfoil with a spoiler and flap was carried out. Results of these studies are presented. The coefficient of lift was seen to decline sharply in the range of spoiler angles ranging from 0 to 15 deg, due to the early separation that the spoiler introduces on the airfoil. Experiments with wing-flap combinations for flap angles ranging from 0 to 45 deg showed that there is an optimum wing-flap gap for a wing-flap configuration. A considerable increase in the intensities of turbulences were seen at higher flap angles that should contribute to the sharp increase in the drag at the higher flap angles. A wake frequency spectrum for varying angles of attack has been made and is presented.
Original language | English |
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Pages (from-to) | 1324-1327 |
Number of pages | 4 |
Journal | Journal of Aircraft |
Volume | 31 |
Issue number | 6 |
DOIs | |
Publication status | Published - 1994 |
ASJC Scopus subject areas
- Aerospace Engineering