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In these equations, g 0, M and R * are each single-valued constants, while ρ, L, T and h are multi-valued constants in accordance with the table below. The values used for M, g 0 and R * are in accordance with the U.S. Standard Atmosphere, 1976, and that the value for R * in particular does not agree with standard values for this constant. [2]
However, its units are traditionally referred to as g, because of the relation between load factor and apparent acceleration of gravity felt on board the aircraft. A load factor of one, or 1 g, represents conditions in straight and level flight, where the lift is equal to the weight.
One g is the force per unit mass due to gravity at the Earth's surface and is the standard gravity (symbol: g n), defined as 9.806 65 metres per second squared, [5] or equivalently 9.806 65 newtons of force per kilogram of mass. The unit definition does not vary with location—the g-force when standing on the Moon is almost exactly 1 ⁄ 6 that
g = acceleration due to gravity at the current location The pressure (force per unit area) at a given altitude is a result of the weight of the overlying atmosphere. If at a height of z the atmosphere has density ρ and pressure P , then moving upwards an infinitesimally small height dz will decrease the pressure by amount dP , equal to the ...
[2] [3] At different points on Earth's surface, the free fall acceleration ranges from 9.764 to 9.834 m/s 2 (32.03 to 32.26 ft/s 2), [4] depending on altitude, latitude, and longitude. A conventional standard value is defined exactly as 9.80665 m/s² (about 32.1740 ft/s²).
For example, considered over the total time-span of Earth (4.6 billion years), a clock set in a geostationary position at an altitude of 9,000 meters above sea level, such as perhaps at the top of Mount Everest (prominence 8,848 m), would be about 39 hours ahead of a clock set at sea level.
V x increases with altitude and V Y decreases with altitude until they converge at the airplane's absolute ceiling, the altitude above which the airplane cannot climb in steady flight. The Cessna 172 is a four-seat aircraft. At maximum weight it has a V Y of 75 kn (139 km/h) indicated airspeed [4] providing a rate of climb of 721 ft/min (3.66 m/s).
For example, the equation above gives the acceleration at 9.820 m/s 2, when GM = 3.986 × 10 14 m 3 /s 2, and R = 6.371 × 10 6 m. The centripetal radius is r = R cos( φ ) , and the centripetal time unit is approximately ( day / 2 π ), reduces this, for r = 5 × 10 6 metres, to 9.79379 m/s 2 , which is closer to the observed value.