"cruising at higher altitudes lowers the AofA for a given indicated airspeed".
I think the above statement is incorrect. The weight of an aircraft and lift required to support it does not change with altitude. Lift is proportional to airspeed, AoA, density and wing design....the basic lift formula we are taught as students. Therefore for a "given airspeed" and weight and wing design that we cannot alter in flight, as density decreases with altitude, AoA must be increased up until the aircraft ceiling is reached when the AoA reaches the stall angle. It is only if power is increased to increase the given speed that the AoA can be reduced. Pleased to be corrected. John John Martindale Unit 39 40 Solitary Islands Way Sapphire Beach NSW 2450 Australia m:0403 432179 email:john_martind...@bigpond.com snip Just thinking out loud here . . . but if angle of attack decreases with an increase of indicated airspeed, and also with a decrease in air density . . . cruising at higher altitudes lowers the AofA for a given indicated airspeed, snip. _______________________________________________ Search the KRnet Archives at https://www.mail-archive.com/krnet@list.krnet.org/. Please see LIST RULES and KRnet info at http://www.krnet.org/info.html. see http://list.krnet.org/mailman/listinfo/krnet_list.krnet.org to change options. To UNsubscribe from KRnet, send a message to krnet-le...@list.krnet.org
