Equivalent Airspeed given Static Pressure Calculator

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Preliminary Aerodynamics

✖Sonic Speed at Sea Level is the speed of sound at sea level.ⓘ Sonic Speed at Sea Level [a_o]			+10% -10%
✖Mach Number (Ma) is a dimensionless quantity that represents the ratio of the speed of an object (such as an aircraft or projectile) to the speed of sound in the surrounding medium.ⓘ Mach Number [M]			+10% -10%
✖Static Pressure is the pressure exerted by a fluid (such as air or a gas) that is not in motion.ⓘ Static Pressure [P_static]			+10% -10%
✖Static Sea Level Pressure is the weight of a column of air with a cross-sectional area of 1 ft^2 and extending upward from sea level through the atmosphere.ⓘ Static Sea Level Pressure [P_o]			+10% -10%

✖Equivalent Airspeed is calibrated airspeed corrected for the compressibility of air at a non-trivial Mach number.ⓘ Equivalent Airspeed given Static Pressure [EAS]

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Formula

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Equivalent Airspeed given Static Pressure

Formula

`"EAS" = "a"_{"o"}*"M"*("P"_{"static"}*6894.7573/"P"_{"o"})^(0.5) `

Example

`"11218.64m/s"="340m/s"*"8"*("250Pa"*6894.7573/"101325Pa")^(0.5) `

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Equivalent Airspeed given Static Pressure Solution

STEP 0: Pre-Calculation Summary

Formula Used

Equivalent Airspeed = Sonic Speed at Sea Level*Mach Number*(Static Pressure*6894.7573/Static Sea Level Pressure)^(0.5)
EAS = a_o*M*(P_static*6894.7573/P_o)^(0.5)
This formula uses 5 Variables

Variables Used

Equivalent Airspeed - (Measured in Meter per Second) - Equivalent Airspeed is calibrated airspeed corrected for the compressibility of air at a non-trivial Mach number.
Sonic Speed at Sea Level - (Measured in Meter per Second) - Sonic Speed at Sea Level is the speed of sound at sea level.
Mach Number - Mach Number (Ma) is a dimensionless quantity that represents the ratio of the speed of an object (such as an aircraft or projectile) to the speed of sound in the surrounding medium.
Static Pressure - (Measured in Pascal) - Static Pressure is the pressure exerted by a fluid (such as air or a gas) that is not in motion.
Static Sea Level Pressure - (Measured in Pascal) - Static Sea Level Pressure is the weight of a column of air with a cross-sectional area of 1 ft^2 and extending upward from sea level through the atmosphere.

STEP 1: Convert Input(s) to Base Unit

Sonic Speed at Sea Level: 340 Meter per Second --> 340 Meter per Second No Conversion Required
Mach Number: 8 --> No Conversion Required
Static Pressure: 250 Pascal --> 250 Pascal No Conversion Required
Static Sea Level Pressure: 101325 Pascal --> 101325 Pascal No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

EAS = a_o*M*(P_static*6894.7573/P_o)^(0.5) --> 340*8*(250*6894.7573/101325)^(0.5)

Evaluating ... ...

EAS = 11218.6369480617

STEP 3: Convert Result to Output's Unit

11218.6369480617 Meter per Second --> No Conversion Required

FINAL ANSWER

11218.6369480617 ≈ 11218.64 Meter per Second <-- Equivalent Airspeed

(Calculation completed in 00.020 seconds)

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< 14 Atmosphere and Gas Properties Calculators

Mach Number given Dynamic Pressure

Go Mach Number = sqrt((2*Dynamic Pressure)/(Ambient Air Density*Heat Capacity Ratio*Specific Gas Constant*Static Temperature))

Ambient Air Density given Mach Number and Temperature

Go Ambient Air Density = (2*Dynamic Pressure)/(Mach Number^2*Heat Capacity Ratio*Specific Gas Constant*Static Temperature)

Temperature given Dynamic Pressure and Mach Number

Go Static Temperature = (2*Dynamic Pressure)/(Ambient Air Density*Mach Number^2*Specific Gas Constant*Heat Capacity Ratio)

Gas constant given dynamic pressure

Go Specific Gas Constant = (2*Dynamic Pressure)/(Ambient Air Density*Mach Number^2*Heat Capacity Ratio*Static Temperature)

Equivalent Airspeed given Static Pressure

Go Equivalent Airspeed = Sonic Speed at Sea Level*Mach Number*(Static Pressure*6894.7573/Static Sea Level Pressure)^(0.5)

Geometric altitude for given geopotential altitude

Go Geometric Altitude = [Earth-R]*Geopotential altitude/([Earth-R]-Geopotential altitude)

Geopotential altitude

Go Geopotential altitude = [Earth-R]*Geometric Altitude/([Earth-R]+Geometric Altitude)

Mach Number given Static and Dynamic Pressure

Go Mach Number = sqrt(2*Dynamic Pressure/(Static Pressure*Heat Capacity Ratio))

Ambient Pressure given Dynamic Pressure and Mach Number

Go Static Pressure = (2*Dynamic Pressure)/(Heat Capacity Ratio*Mach Number^2)

Ambient air density given mach number

Go Ambient Air Density = 2*Dynamic Pressure/(Mach Number*Sonic Speed)^2

Ambient air density given dynamic pressure

Go Ambient Air Density = 2*Dynamic Pressure/(Flight Speed^2)

Lapse rate

Go Lapse Rate = Change in Temperature/Altitude difference

Geometric altitude

Go Geometric Altitude = Absolute Altitude-[Earth-R]

Absolute altitude

Go Absolute Altitude = Geometric Altitude+[Earth-R]

Equivalent Airspeed given Static Pressure Formula

Equivalent Airspeed = Sonic Speed at Sea Level*Mach Number*(Static Pressure*6894.7573/Static Sea Level Pressure)^(0.5)
EAS = a_o*M*(P_static*6894.7573/P_o)^(0.5)

What is a Mach Number?

Mach number M is defined as the ratio of the true airspeed V to the speed of sound and in the air at the flight altitude.

What is meant by static pressure?

The static pressure (or, simply, pressure) is the pressure that a fluid exerts when it is not moving.

How to Calculate Equivalent Airspeed given Static Pressure?

Equivalent Airspeed given Static Pressure calculator uses Equivalent Airspeed = Sonic Speed at Sea Level*Mach Number*(Static Pressure*6894.7573/Static Sea Level Pressure)^(0.5) to calculate the Equivalent Airspeed, The Equivalent Airspeed given Static Pressure formula is defined as the speed at sea level, under ISA conditions, that would produce the same incompressible dynamic pressure that is produced at the true airspeed for the given aircraft altitude. Equivalent Airspeed is denoted by EAS symbol.

How to calculate Equivalent Airspeed given Static Pressure using this online calculator? To use this online calculator for Equivalent Airspeed given Static Pressure, enter Sonic Speed at Sea Level (a_o), Mach Number (M), Static Pressure (P_static) & Static Sea Level Pressure (P_o) and hit the calculate button. Here is how the Equivalent Airspeed given Static Pressure calculation can be explained with given input values -> 11218.64 = 340*8*(250*6894.7573/101325)^(0.5) .

FAQ

What is Equivalent Airspeed given Static Pressure?

The Equivalent Airspeed given Static Pressure formula is defined as the speed at sea level, under ISA conditions, that would produce the same incompressible dynamic pressure that is produced at the true airspeed for the given aircraft altitude and is represented as EAS = a_o*M*(P_static*6894.7573/P_o)^(0.5) or Equivalent Airspeed = Sonic Speed at Sea Level*Mach Number*(Static Pressure*6894.7573/Static Sea Level Pressure)^(0.5). Sonic Speed at Sea Level is the speed of sound at sea level, Mach Number (Ma) is a dimensionless quantity that represents the ratio of the speed of an object (such as an aircraft or projectile) to the speed of sound in the surrounding medium, Static Pressure is the pressure exerted by a fluid (such as air or a gas) that is not in motion & Static Sea Level Pressure is the weight of a column of air with a cross-sectional area of 1 ft^2 and extending upward from sea level through the atmosphere.

How to calculate Equivalent Airspeed given Static Pressure?

The Equivalent Airspeed given Static Pressure formula is defined as the speed at sea level, under ISA conditions, that would produce the same incompressible dynamic pressure that is produced at the true airspeed for the given aircraft altitude is calculated using Equivalent Airspeed = Sonic Speed at Sea Level*Mach Number*(Static Pressure*6894.7573/Static Sea Level Pressure)^(0.5). To calculate Equivalent Airspeed given Static Pressure, you need Sonic Speed at Sea Level (a_o), Mach Number (M), Static Pressure (P_static) & Static Sea Level Pressure (P_o). With our tool, you need to enter the respective value for Sonic Speed at Sea Level, Mach Number, Static Pressure & Static Sea Level Pressure and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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