What is the relationship between pressure, altitude, and temperature at Standard Temperature and Pressure?

Answer 1

A relationship as derived from the Poisson Potential Temperature equation and the hydrostatic approximation is as follows:

Z = (Rd/g) * ln(p1/p2) * T

where:
Z: altitude in meters
Rd: dry gas constant = 287 J/(kgK)
g: gravity = 9.8 (m/s2)
p1: standard pressure/sfc pressure = 1000 hPa
p2: the pressure at the altitude in mb or hPa
T: average temperature between the altitude and the ground (a very rough estimate = 273K)

There are no very accurate equations for determining the altitude using solely surface dynamics ( i.e. standard temp and pressure), instead you must take into consideration the entire atmosphere between the ground and the level at which you're interested in.

The only two variables you should need to input for this equation are p2 and T, which can be determined using a skew T plot assessed twice daily at select US and Canadian locations from balloons.

Since this is probably a little too in depth, a simplier, approximated equation based on the one above is as follows:

p2 = p1 * e^(Z/H)

where:
Z, p2, p1 are the same as above
H: scale height of the atmosphere roughly = 8000 m

all you need for this is p2, the pressure at the desired altitude.
Remember the atmosphere itself is mess when it comes to variables, approximations however usually fair well.

Hope this helps

Answer 2

The relation between the pressure,altitude and temperature can be given by Z=221T(logP1--logP2) where Z is the altitude,T and P2 is the absolute temperature and pressure at the height Z respectively.P1 is the surface pressure.

Answer 3

Aviators degree velocity in numerous distinctive techniques. The gadgets they use are knots (= nautical miles in line with hour) and Mach numbers (= velocity relative to the fee of sound). Indicated airspeed is the fee shown on the airspeed indicator in the cockpit. as a results of way air density and different factors impact the device used to degree airspeed, indicated airspeed is regularly somewhat below real airspeed (the certainly velocity of the plane relative to the air around it). real airspeed is the certainly velocity of the plane in the time of the air around it. floor velocity is the fee of the plane relative to the floor (which may be distinctive from real airspeed, if there's a wind blowing). those speeds are regularly measured in nautical miles in line with hour, in any different case universal as knots. At severe altitudes and airspeeds, they are greater generally measured in Mach numbers. Mach a million.0 is the fee of sound, Mach 0.5 is 0.5 the fee of sound, Mach 2.0 is two times the fee of sound, and so on. the fee of sound isn't consistent—it varies with air temperature (specifically). as a result, the courting between knots and airspeed differences with altitude, temperature, and so on. Mach 0.seventy 8 is for this reason distinctive at 40,000 ft than that's at 10,000 ft. And an indicated airspeed of three hundred knots is distinctive at 10,000 ft from what it may be at 20,000 ft. real airspeed is an identical in any respect altitudes. the version in Mach effects from the variations in the certainly velocity of sound below distinctive situations; the version in indicated airspeed effects from the way airspeed measurement structures attempt to degree airspeed. real airspeed does not substitute, however the calculations required to get real airspeed from indicated airspeed in knots or Mach numbers substitute with atmospheric situations.