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a) Show that the trimmed static stability requirement ac > Icg is equivalent to the requirement that dcm,cg/da < 0, where Cm,cg is the moment coefficient about the center of gravity. Assume that lift increases with angle of attack. Relate dcm,cg/da to the static stability margin, SM = (xac-cg)/c, and the lift-curve slope, de₁/da. Note, do not assume thin airfoil theory. b) Calculate the trimmed static-stability margin of a NACA 4416 airfoil at c₁ = 0.5 using mfoil. Do this first with no flap and then again with a flap hinged at 80% chord, deflected 15° down. Include pressure coefficient plots and discuss the results.

a) Show that the trimmed static stability requirement ac > Icg is equivalent to the requirement that dcm,cg/da < 0, where Cm,cg is the moment coefficient about the center of gravity. Assume that lift increases with angle of attack. Relate dcm,cg/da to the static stability margin, SM = (xac-cg)/c, and the lift-curve slope, de₁/da. Note, do not assume thin airfoil theory. b) Calculate the trimmed static-stability margin of a NACA 4416 airfoil at c₁ = 0.5 using mfoil. Do this first with no flap and then again with a flap hinged at 80% chord, deflected 15° down. Include pressure coefficient plots and discuss the results.

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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a) Show that the trimmed static stability requirement ac > Icg is equivalent to the requirement that dcm,cg/da < 0, where Cm,cg is the moment coefficient about the center of gravity. Assume that lift increases with angle of attack. Relate dcm,cg/da to the static stability margin, SM = (xac-cg)/c, and the lift-curve slope, de₁/da. Note, do not assume thin airfoil theory. b) Calculate the trimmed static-stability margin of a NACA 4416 airfoil at c₁ = 0.5 using mfoil. Do this first with no flap and then again with a flap hinged at 80% chord, deflected 15° down. Include pressure coefficient plots and discuss the results.
Transcribed Image Text:a) Show that the trimmed static stability requirement ac > Icg is equivalent to the requirement that dcm,cg/da < 0, where Cm,cg is the moment coefficient about the center of gravity. Assume that lift increases with angle of attack. Relate dcm,cg/da to the static stability margin, SM = (xac-cg)/c, and the lift-curve slope, de₁/da. Note, do not assume thin airfoil theory. b) Calculate the trimmed static-stability margin of a NACA 4416 airfoil at c₁ = 0.5 using mfoil. Do this first with no flap and then again with a flap hinged at 80% chord, deflected 15° down. Include pressure coefficient plots and discuss the results.
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