Study of an airfoil with a flap and spoiler

Abdullah Al Shabibi, Munir Al Hammadi, Joseph Mathew

Research output: Contribution to journalArticle


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 languageEnglish
Pages (from-to)1324-1327
Number of pages4
JournalJournal of Aircraft
Issue number6
Publication statusPublished - Nov 1994

ASJC Scopus subject areas

  • Aerospace Engineering

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    Shabibi, A. A., Hammadi, M. A., & Mathew, J. (1994). Study of an airfoil with a flap and spoiler. Journal of Aircraft, 31(6), 1324-1327.