Dynamic pressure given induced drag Calculator

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Lift and Drag Polar

✖The lift force, lifting force or simply lift is the sum of all the forces on a body that force it to move perpendicular to the direction of flow.ⓘ Lift Force [F_L]			+10% -10%
✖Induced drag is caused by that element of the air deflected downward which is not vertical to the flight path but is tilted slightly rearward from it.ⓘ Induced Drag [D_i]			+10% -10%
✖Lateral plane span is set of all linear combinations of 2 non-parallel vectors u and v is called the span of u and v.ⓘ Lateral plane span [b_W]			+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 given induced drag [q]

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Formula

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Dynamic pressure given induced drag

Formula

`"q" = "F"_{"L"}^2/(pi*"D"_{"i"}*"b"_{"W"}^2)`

Example

`"70.54406Pa"=("20.45N")^2/(pi*"1.2N"*("1.254m")^2)`

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Dynamic pressure given induced drag Solution

STEP 0: Pre-Calculation Summary

Formula Used

Dynamic Pressure = Lift Force^2/(pi*Induced Drag*Lateral plane span^2)
q = F_L^2/(pi*D_i*b_W^2)
This formula uses 1 Constants, 4 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

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.
Lift Force - (Measured in Newton) - The lift force, lifting force or simply lift is the sum of all the forces on a body that force it to move perpendicular to the direction of flow.
Induced Drag - (Measured in Newton) - Induced drag is caused by that element of the air deflected downward which is not vertical to the flight path but is tilted slightly rearward from it.
Lateral plane span - (Measured in Meter) - Lateral plane span is set of all linear combinations of 2 non-parallel vectors u and v is called the span of u and v.

STEP 1: Convert Input(s) to Base Unit

Lift Force: 20.45 Newton --> 20.45 Newton No Conversion Required
Induced Drag: 1.2 Newton --> 1.2 Newton No Conversion Required
Lateral plane span: 1.254 Meter --> 1.254 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

q = F_L^2/(pi*D_i*b_W^2) --> 20.45^2/(pi*1.2*1.254^2)

Evaluating ... ...

q = 70.5440570910867

STEP 3: Convert Result to Output's Unit

70.5440570910867 Pascal --> No Conversion Required

FINAL ANSWER

70.5440570910867 ≈ 70.54406 Pascal <-- Dynamic Pressure

(Calculation completed in 00.004 seconds)

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

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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 given induced drag Formula

Dynamic Pressure = Lift Force^2/(pi*Induced Drag*Lateral plane span^2)
q = F_L^2/(pi*D_i*b_W^2)

What is dynamic pressure?

Dynamic pressure is the kinetic energy per unit volume of a fluid. Dynamic pressure is one of the terms of Bernoulli's equation, which can be derived from the conservation of energy for a fluid in motion.

How to Calculate Dynamic pressure given induced drag?

Dynamic pressure given induced drag calculator uses Dynamic Pressure = Lift Force^2/(pi*Induced Drag*Lateral plane span^2) to calculate the Dynamic Pressure, The Dynamic pressure given induced drag formula is defined as the pressure exerted on the aircraft under the influence of the lift force and induced drag. Dynamic Pressure is denoted by q symbol.

How to calculate Dynamic pressure given induced drag using this online calculator? To use this online calculator for Dynamic pressure given induced drag, enter Lift Force (F_L), Induced Drag (D_i) & Lateral plane span (b_W) and hit the calculate button. Here is how the Dynamic pressure given induced drag calculation can be explained with given input values -> 70.6567 = 20.45^2/(pi*1.2*1.254^2).

FAQ

What is Dynamic pressure given induced drag?

The Dynamic pressure given induced drag formula is defined as the pressure exerted on the aircraft under the influence of the lift force and induced drag and is represented as q = F_L^2/(pi*D_i*b_W^2) or Dynamic Pressure = Lift Force^2/(pi*Induced Drag*Lateral plane span^2). The lift force, lifting force or simply lift is the sum of all the forces on a body that force it to move perpendicular to the direction of flow, Induced drag is caused by that element of the air deflected downward which is not vertical to the flight path but is tilted slightly rearward from it & Lateral plane span is set of all linear combinations of 2 non-parallel vectors u and v is called the span of u and v.

How to calculate Dynamic pressure given induced drag?

The Dynamic pressure given induced drag formula is defined as the pressure exerted on the aircraft under the influence of the lift force and induced drag is calculated using Dynamic Pressure = Lift Force^2/(pi*Induced Drag*Lateral plane span^2). To calculate Dynamic pressure given induced drag, you need Lift Force (F_L), Induced Drag (D_i) & Lateral plane span (b_W). With our tool, you need to enter the respective value for Lift Force, Induced Drag & Lateral plane span 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 Lift Force, Induced Drag & Lateral plane span. 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*Flight speed^2
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

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