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10 results for “altitude”

Formulae (10)

TAS \approx IAS + (IAS \times 0.02 \times \tfrac{alt}{1000})

Quick estimate: true airspeed increases about 2% per 1000 ft of altitude above indicated airspeed.

ROC = \dfrac{\Delta h}{t}

Vertical speed is the altitude gained per unit time (ft per minute).

PA = (29.92 - QNH)\times 1000 + h

Altitude referenced to standard pressure; correct field elevation for the altimeter setting.

DA = PA + 120(OAT - ISA_{temp})

Pressure altitude corrected for non-standard temperature; higher DA reduces performance.

GR = \dfrac{d}{h} = \dfrac{L}{D}

Horizontal distance traveled per unit of altitude lost equals the lift-to-drag ratio.

h = \dfrac{RT}{g}\ln\dfrac{P_0}{P}

Altitude derived from the ratio of sea-level to measured pressure.

GR = \frac{\text{horizontal distance}}{\text{altitude lost}}

Distance traveled forward per unit of height lost.

TAS \approx IAS\left(1 + \frac{h}{60000}\right)

Airspeed corrected for altitude.

DA = PA + 120(OAT - ISA)

Pressure altitude corrected for temperature.

P = P_0 e^{-\frac{Mgh}{RT}}

Atmospheric pressure as a function of altitude.