ملخص
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.
اللغة الأصلية | English |
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الصفحات (من إلى) | 1324-1327 |
عدد الصفحات | 4 |
دورية | Journal of Aircraft |
مستوى الصوت | 31 |
رقم الإصدار | 6 |
المعرِّفات الرقمية للأشياء | |
حالة النشر | Published - 1994 |
ASJC Scopus subject areas
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