Study of an airfoil with a flap and spoiler

Abdullah Al Shabibi, Munir Al Hammadi, Joseph Mathew

نتاج البحث: المساهمة في مجلةمقالمراجعة النظراء


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 الأصليةEnglish
الصفحات (من إلى)1324-1327
عدد الصفحات4
دوريةJournal of Aircraft
مستوى الصوت31
رقم الإصدار6
المعرِّفات الرقمية للأشياء
حالة النشرPublished - 1994

ASJC Scopus subject areas

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