Dynamic pressure aircraft Calculator

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Introduction and Governing Equations

Aircraft Design

Aircraft Performance

Static Stability and Control

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Preliminary Aerodynamics

Aircraft Dynamics Nomenclature

Atmosphere and Gas Properties

Lift and Drag Polar

✖Ambient air density is the mass per unit volume of Earth's atmosphere.ⓘ Ambient air density [ρ]			+10% -10%
✖Flight speed is defined as an airspeed sufficient to provide the lift necessary to support an airplane in level flight.ⓘ Flight speed [V_fs]			+10% -10%

✖Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.ⓘ Dynamic pressure aircraft [q]

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Formula

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Dynamic pressure aircraft

Formula

`"q" = 1/2*"ρ"*"V"_{"fs"}^2`

Example

`"70.5189Pa"=1/2*"1.225kg/m³"*("10.73m/s")^2`

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Dynamic pressure aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Dynamic Pressure = 1/2*Ambient air density*Flight speed^2
q = 1/2*ρ*V_fs^2
This formula uses 3 Variables

Variables Used

Dynamic Pressure - (Measured in Pascal) - Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.
Ambient air density - (Measured in Kilogram per Cubic Meter) - Ambient air density is the mass per unit volume of Earth's atmosphere.
Flight speed - (Measured in Meter per Second) - Flight speed is defined as an airspeed sufficient to provide the lift necessary to support an airplane in level flight.

STEP 1: Convert Input(s) to Base Unit

Ambient air density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Flight speed: 10.73 Meter per Second --> 10.73 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

q = 1/2*ρ*V_fs^2 --> 1/2*1.225*10.73^2

Evaluating ... ...

q = 70.51890125

STEP 3: Convert Result to Output's Unit

70.51890125 Pascal --> No Conversion Required

FINAL ANSWER

70.51890125 ≈ 70.5189 Pascal <-- Dynamic Pressure

(Calculation completed in 00.007 seconds)

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Created by Himanshu Sharma

National Institute of Technology, Hamirpur (NITH), Himachal Pradesh

Himanshu Sharma has created this Calculator and 50+ more calculators!

Verified by Kartikay Pandit

National Institute Of Technology (NIT), Hamirpur

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< 17 Preliminary Aerodynamics Calculators

Power required at sea-level conditions

Go Power required at sea-level = sqrt((2*Weight of body^3*Drag Coefficient^2)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient^3))

Mach Number-2

Go Mach number 2 = sqrt(((((Heat Capacity Ratio-1)*Mach Number^(2)+2))/(2*Heat Capacity Ratio*Mach Number^(2)-(Heat Capacity Ratio-1))))

Power required at Altitude

Go Power required at an altitude = sqrt((2*Weight of body^3*Drag Coefficient^2)/(Density*Reference Area*Lift Coefficient^3))

Velocity at Sea-level given Lift Coefficient

Go Velocity at sea-level = sqrt((2*Weight of body)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient))

Dynamic pressure given gas constant

Go Dynamic Pressure = 1/2*Ambient air density*Mach Number^2*Specific Heat of Air*Gas Constant*Temperature

Velocity at Altitude

Go Velocity at an altitude = sqrt(2*Weight of body/(Density*Reference Area*Lift Coefficient))

Power required at Altitude given Power at sea-level

Go Power required at an altitude = Power required at sea-level*sqrt([Std-Air-Density-Sea]/Density)

Velocity at Altitude given Velocity at Sea-Level

Go Velocity at an altitude = Velocity at sea-level*sqrt([Std-Air-Density-Sea]/Density)

Dynamic pressure given induced drag

Go Dynamic Pressure = Lift Force^2/(pi*Induced Drag*Lateral plane span^2)

Dynamic pressure given mach number

Go Dynamic Pressure = 1/2*Ambient air density*(Mach Number*Sonic speed)^2

Dynamic pressure given normal pressure

Go Dynamic Pressure = 1/2*Specific Heat of Air*Pressure*Mach Number^2

Flight speed given dynamic pressure

Go Flight speed = sqrt((2*Dynamic Pressure)/Ambient air density)

Dynamic pressure aircraft

Go Dynamic Pressure = 1/2*Ambient air density*Flight speed^2

Dynamic pressure given lift coefficient

Go Dynamic Pressure = Lift Force/Lift Coefficient

Dynamic pressure given drag coefficient

Go Dynamic Pressure = Drag Force/Drag Coefficient

Aerodynamic force

Go Aerodynamic Force = Drag Force+Lift Force

Mach number of moving object

Go Mach Number = Velocity/Speed of Sound

Dynamic pressure aircraft Formula

Dynamic Pressure = 1/2*Ambient air density*Flight speed^2
q = 1/2*ρ*V_fs^2

What is dynamic pressure?

Dynamic pressure on a surface at which a flowing fluid is brought to rest in excess of the pressure on it when the fluid is not flowing.

How to Calculate Dynamic pressure aircraft?

Dynamic pressure aircraft calculator uses Dynamic Pressure = 1/2*Ambient air density*Flight speed^2 to calculate the Dynamic Pressure, The Dynamic pressure aircraft formula can be used to determine the airspeed of the aircraft using air density and speed. Dynamic Pressure is denoted by q symbol.

How to calculate Dynamic pressure aircraft using this online calculator? To use this online calculator for Dynamic pressure aircraft, enter Ambient air density (ρ) & Flight speed (V_fs) and hit the calculate button. Here is how the Dynamic pressure aircraft calculation can be explained with given input values -> 27528.2 = 1/2*1.225*10.73^2.

FAQ

What is Dynamic pressure aircraft?

The Dynamic pressure aircraft formula can be used to determine the airspeed of the aircraft using air density and speed and is represented as q = 1/2*ρ*V_fs^2 or Dynamic Pressure = 1/2*Ambient air density*Flight speed^2. Ambient air density is the mass per unit volume of Earth's atmosphere & Flight speed is defined as an airspeed sufficient to provide the lift necessary to support an airplane in level flight.

How to calculate Dynamic pressure aircraft?

The Dynamic pressure aircraft formula can be used to determine the airspeed of the aircraft using air density and speed is calculated using Dynamic Pressure = 1/2*Ambient air density*Flight speed^2. To calculate Dynamic pressure aircraft, you need Ambient air density (ρ) & Flight speed (V_fs). With our tool, you need to enter the respective value for Ambient air density & Flight speed and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Dynamic Pressure?

In this formula, Dynamic Pressure uses Ambient air density & Flight speed. We can use 6 other way(s) to calculate the same, which is/are as follows -

Dynamic Pressure = Lift Force/Lift Coefficient
Dynamic Pressure = Drag Force/Drag Coefficient
Dynamic Pressure = 1/2*Ambient air density*(Mach Number*Sonic speed)^2
Dynamic Pressure = 1/2*Ambient air density*Mach Number^2*Specific Heat of Air*Gas Constant*Temperature
Dynamic Pressure = 1/2*Specific Heat of Air*Pressure*Mach Number^2
Dynamic Pressure = Lift Force^2/(pi*Induced Drag*Lateral plane span^2)

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