some info. at :48, profile/airfoil thickness IS expressed as a Percentage of main wing chord length. when a (tiny) airfoil is made less than 11.7 percent thick, the wing will have a higher stall speed; and will Require a higher cruising airspeed (in order to make sufficient Lift). at 1:45, main half-spars and the Thickest point of the profile are located at THIRTY percent of chord. in the case of a swept wing, cg Must be located at mac. mean aerodynamic chord. mac aligns with 45 to 50 percent of (swept wing) Root chord. at the linked diagram, the concept is shown; but the DETAILS are wrong. the reference line is at THIRTY percent of chord; NOT 25. when the mean point is determined, mac will Align with a point located aft-of thirty percent of root chord. googletranslate image3.slideserve.com/6772151/mean-aerodynamic-chord-l.jpg
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some info. at :48, profile/airfoil thickness IS expressed as a Percentage of main wing chord length. when a (tiny) airfoil is made less than 11.7 percent thick, the wing will have a higher stall speed; and will Require a higher cruising airspeed (in order to make sufficient Lift). at 1:45, main half-spars and the Thickest point of the profile are located at THIRTY percent of chord. in the case of a swept wing, cg Must be located at mac. mean aerodynamic chord. mac aligns with 45 to 50 percent of (swept wing) Root chord. at the linked diagram, the concept is shown; but the DETAILS are wrong. the reference line is at THIRTY percent of chord; NOT 25. when the mean point is determined, mac will Align with a point located aft-of thirty percent of root chord. googletranslate
image3.slideserve.com/6772151/mean-aerodynamic-chord-l.jpg