Study of an airfoil with a flap and spoiler

Abdullah Al Shabibi, Munir Al Hammadi, Joseph Mathew

Research output: Contribution to journalArticle

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 languageEnglish
Pages (from-to)1324-1327
Number of pages4
JournalJournal of Aircraft
Volume31
Issue number6
Publication statusPublished - Nov 1994

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Flaps
Airfoils
Angle of attack
Drag
Turbulence
Experiments

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

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.

Study of an airfoil with a flap and spoiler. / Shabibi, Abdullah Al; Hammadi, Munir Al; Mathew, Joseph.

In: Journal of Aircraft, Vol. 31, No. 6, 11.1994, p. 1324-1327.

Research output: Contribution to journalArticle

Shabibi, AA, Hammadi, MA & Mathew, J 1994, 'Study of an airfoil with a flap and spoiler', Journal of Aircraft, vol. 31, no. 6, pp. 1324-1327.
Shabibi AA, Hammadi MA, Mathew J. Study of an airfoil with a flap and spoiler. Journal of Aircraft. 1994 Nov;31(6):1324-1327.
Shabibi, Abdullah Al ; Hammadi, Munir Al ; Mathew, Joseph. / Study of an airfoil with a flap and spoiler. In: Journal of Aircraft. 1994 ; Vol. 31, No. 6. pp. 1324-1327.
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