This whole CG thing comes down to the following simple law of physics:
Any lifting body (wing) has a center of lift (CL) where if all areas of lift were concentrated in to one spot, it is the CL The engineer designs the airplane to distribute the weight of the aircraft so that if all weight is combined (CG)it is located at the center of lift. That could only be done for a single flight scenario, one were nothing changes from takeoff to landing. That not being possible, a rear mounted horizontal stabilizer / elevator or a forward mounted canard is added to balance the aircraft when the CG moves forward or rearward from the CL or the CL moves forward or rearward on the wing (angle of attack, flap deployment, etc). The CG range is determined by the size of these control surfaces, their amount of possible movement, and their distance from the CL. It is a simple law of physics, think teeter totter , but not that easily accomplished in an airplane were CL and CG can or is constantly changing.
Bottom line, if you plan to make changes in wing size, shape, flaps, ailerons, etc., or tail sizes, fuselage length, and all those things, know what effect it will have on aircraft handling. If you're not sure, stick to the plans and accept flight proven flight characteristics.
Larry Flesner _______________________________________________ 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
