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Center of Gravity (CG) is the point where the weight of the aircraft is balanced. Neutral Point (NP) is the point where the aerodynamic forces of the wing and tail are balanced. 25% - 35% MAC is the typical range for the CG of a conventional aircraft. Placing CG 5% to 15% of MAC in front of NP creates a longitudinal (pitch) stability called Static Margin. A lower margin (tail heavy) produces less stability and greater elevator authority, while a higher margin (nose heavy) creates more stability and less elevator authority. A static margin that's too high may result in elevator stall at take off and landing. Vbar is a unitless volume coefficient, based on the ratio of the wing surface area to the horizontal tail group (stabilizer and elevator) surface area and the distance between the wing's AC and the tail's AC.

It quantifies the tail's aerodynamic effectiveness and is used to calculate NP. Typical values range from 0.35 (smaller or closer to the wing, thus less effective) to 0.6 (larger or farther from the wing, thus more effective). COPYRIGHT NOTICES:.

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CG & MAC equations adapted from the Public Domain. NP equations courtesy (see C.G. Position article on ). Neutral Point and Weight & Balance Calculators developed by Dean A.

Scott and are (c) 2005 -, all rights reserved. Unauthorized use of the codebehind, html, or content is strictly prohibitied. Additional thanks to Geoff Haynes, vice-president, HMAC, for refinements to the code. Email the author at dascott / at / chrusion / dot / com to obtain copyright clearances to redistribute, repurpose, and/or reuse all or parts of the code and content herein.

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Last updated 03 Sep 2018.