Is EAS directly proportional to drag?
Came across a book where it says, air frame cruise drag decreases with an increase in higher altitudes. This is mainly because we fly at a constant mach number above FL260. With a constant mach number EAS decreases with an increase in altitude. Hence drag decreases, as EAS is directly proportional to drag.
I get how EAS decreases with increase in altitude with constant MN. Don't understand how EAS is directly proportional to drag.
Last edited by SuperflyTNT; 6th April 2013 at 12:04.