Starflight
Well-Known Member
Looking through the airfoil performance tables of a previously
mentioned textbook, I noticed a specification of dCl/da (change
of Cl divided by change of angle of attack). In the spectrum of
ultralight design, is it preferable to have a higher value (steeper,
faster rise of curve=lower stall angle) than the lower slope, high
AOA of stall? I have found several airfoils that have equal Clmax
but quite different curve slopes. My preference for very low powered
ULs would be the lower STALL angle to maintain control and make the
best use of available power, all other parameters being equal. Is
this assumption correct or would control be compromised in high
G maneuvers (steep turns, flare roundout etc.)?
mentioned textbook, I noticed a specification of dCl/da (change
of Cl divided by change of angle of attack). In the spectrum of
ultralight design, is it preferable to have a higher value (steeper,
faster rise of curve=lower stall angle) than the lower slope, high
AOA of stall? I have found several airfoils that have equal Clmax
but quite different curve slopes. My preference for very low powered
ULs would be the lower STALL angle to maintain control and make the
best use of available power, all other parameters being equal. Is
this assumption correct or would control be compromised in high
G maneuvers (steep turns, flare roundout etc.)?
