Free Stream Velocity over Flat Plate using Drag Force Calculator

✖Drag Force is the resisting force experienced by an object moving through a fluid.ⓘ Drag Force [F_D]			+10% -10%
✖Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.ⓘ Freestream density [ρ_∞]			+10% -10%
✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+10% -10%
✖Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.ⓘ Drag Coefficient [C_D]			+10% -10%

✖The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air.ⓘ Free Stream Velocity over Flat Plate using Drag Force [V_∞]

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Formula

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Free Stream Velocity over Flat Plate using Drag Force

Formula

`"V"_{"∞"} = sqrt("F"_{"D"}/(0.5*"ρ"_{"∞"}*"S"*"C"_{"D"}))`

Example

`"2.643438m/s"=sqrt("82N"/(0.5*"2.1kg/m³"*"5.08m²"*"2.2"))`

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Free Stream Velocity over Flat Plate using Drag Force Solution

STEP 0: Pre-Calculation Summary

Formula Used

Freestream Velocity = sqrt(Drag Force/(0.5*Freestream density*Reference Area*Drag Coefficient))
V_∞ = sqrt(F_D/(0.5*ρ_∞*S*C_D))
This formula uses 1 Functions, 5 Variables

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)

Variables Used

Freestream Velocity - (Measured in Meter per Second) - The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air.
Drag Force - (Measured in Newton) - Drag Force is the resisting force experienced by an object moving through a fluid.
Freestream density - (Measured in Kilogram per Cubic Meter) - Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
Drag Coefficient - Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.

STEP 1: Convert Input(s) to Base Unit

Drag Force: 82 Newton --> 82 Newton No Conversion Required
Freestream density: 2.1 Kilogram per Cubic Meter --> 2.1 Kilogram per Cubic Meter No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Drag Coefficient: 2.2 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

V_∞ = sqrt(F_D/(0.5*ρ_∞*S*C_D)) --> sqrt(82/(0.5*2.1*5.08*2.2))

Evaluating ... ...

V_∞ = 2.64343770368713

STEP 3: Convert Result to Output's Unit

2.64343770368713 Meter per Second --> No Conversion Required

FINAL ANSWER

2.64343770368713 ≈ 2.643438 Meter per Second <-- Freestream Velocity

(Calculation completed in 00.004 seconds)

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Home » Engineering » Mechanical » Fluid Mechanics » Hypersonic Flow » Flat Plate for Viscous Flow Case » Approximate Results Applied to Hypersonic Vehicles » Free Stream Velocity over Flat Plate using Drag Force

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Amrita School of Engineering (ASE), Vallikavu

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< 15 Approximate Results Applied to Hypersonic Vehicles Calculators

Freestream Velocity over Flat Plate using Stanton Number

Go Freestream Velocity = Local Heat Transfer Rate/(Stanton Number*Freestream density*(Adiabatic Wall Enthalpy-Wall Enthalpy))

Freestream Density over Flat Plate using Stanton Number

Go Freestream density = Local Heat Transfer Rate/(Stanton Number*Freestream Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))

Freestream Stanton Number for Flat Plate

Go Stanton Number = Local Heat Transfer Rate/(Freestream density*Freestream Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))

Adiabatic Wall Enthalpy over Flat Plate using Stanton Number

Go Adiabatic Wall Enthalpy = Local Heat Transfer Rate/(Freestream density*Freestream Velocity*Stanton Number)+Wall Enthalpy

Local Heat Transfer over Flat Plate using Stanton Number

Go Local Heat Transfer Rate = Stanton Number*Freestream density*Freestream Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)

Wall Enthalpy over Flat Plate using Stanton Number

Go Wall Enthalpy = Adiabatic Wall Enthalpy-Local Heat Transfer Rate/(Freestream density*Freestream Velocity*Stanton Number)

Free Stream Velocity over Flat Plate using Drag Force

Go Freestream Velocity = sqrt(Drag Force/(0.5*Freestream density*Reference Area*Drag Coefficient))

Coefficient of Drag over Flat under Freestream Flow Conditions

Go Drag Coefficient = Drag Force/(0.5*Freestream density*Freestream Velocity^2*Reference Area)

Freestream Density over Flat under Freestream Flow Conditions

Go Freestream density = Drag Force/(0.5*Drag Coefficient*Freestream Velocity^2*Reference Area)

Drag Force over Flat Plate

Go Drag Force = 0.5*Freestream density*Freestream Velocity^2*Reference Area*Drag Coefficient

Free Stream Velocity over Flat Plate with Freestream Conditions

Go Freestream Velocity = sqrt(2*(Total Specific Enthalpy-Freestream Specific Enthalpy))

Pressure Ratio for Insulated Flat Plate, Weak Interaction

Go Pressure Ratio = 1+0.31*Viscous Interaction Similarity Parameter+0.05*Viscous Interaction Similarity Parameter^2

Free Stream Enthalpy over Flat Plate with Freestream Conditions

Go Freestream Specific Enthalpy = Total Specific Enthalpy-(Freestream Velocity^2)/2

Total Enthalpy over Flat Plate with Freestream Conditions

Go Total Specific Enthalpy = Freestream Specific Enthalpy+(Freestream Velocity^2)/2

Pressure Ratio for Insulated Flat Plate, Strong Interaction

Go Pressure Ratio = 0.514*Viscous Interaction Similarity Parameter+0.759

Free Stream Velocity over Flat Plate using Drag Force Formula

Freestream Velocity = sqrt(Drag Force/(0.5*Freestream density*Reference Area*Drag Coefficient))
V_∞ = sqrt(F_D/(0.5*ρ_∞*S*C_D))

What is drag force?

A drag force is the resistance force caused by the motion of a body through a fluid, such as water or air. A drag force acts opposite to the direction of the oncoming flow velocity.

How to Calculate Free Stream Velocity over Flat Plate using Drag Force?

Free Stream Velocity over Flat Plate using Drag Force calculator uses Freestream Velocity = sqrt(Drag Force/(0.5*Freestream density*Reference Area*Drag Coefficient)) to calculate the Freestream Velocity, The Free stream velocity over flat plate using drag force formula is defined as the function of freestream density, freestream velocity, reference area, and drag coefficient. Freestream Velocity is denoted by V_∞ symbol.

How to calculate Free Stream Velocity over Flat Plate using Drag Force using this online calculator? To use this online calculator for Free Stream Velocity over Flat Plate using Drag Force, enter Drag Force (F_D), Freestream density (ρ_∞), Reference Area (S) & Drag Coefficient (C_D) and hit the calculate button. Here is how the Free Stream Velocity over Flat Plate using Drag Force calculation can be explained with given input values -> 2.643438 = sqrt(82/(0.5*2.1*5.08*2.2)).

FAQ

What is Free Stream Velocity over Flat Plate using Drag Force?

The Free stream velocity over flat plate using drag force formula is defined as the function of freestream density, freestream velocity, reference area, and drag coefficient and is represented as V_∞ = sqrt(F_D/(0.5*ρ_∞*S*C_D)) or Freestream Velocity = sqrt(Drag Force/(0.5*Freestream density*Reference Area*Drag Coefficient)). Drag Force is the resisting force experienced by an object moving through a fluid, Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area & Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.

How to calculate Free Stream Velocity over Flat Plate using Drag Force?

The Free stream velocity over flat plate using drag force formula is defined as the function of freestream density, freestream velocity, reference area, and drag coefficient is calculated using Freestream Velocity = sqrt(Drag Force/(0.5*Freestream density*Reference Area*Drag Coefficient)). To calculate Free Stream Velocity over Flat Plate using Drag Force, you need Drag Force (F_D), Freestream density (ρ_∞), Reference Area (S) & Drag Coefficient (C_D). With our tool, you need to enter the respective value for Drag Force, Freestream density, Reference Area & Drag Coefficient 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 Freestream Velocity?

In this formula, Freestream Velocity uses Drag Force, Freestream density, Reference Area & Drag Coefficient. We can use 2 other way(s) to calculate the same, which is/are as follows -

Freestream Velocity = Local Heat Transfer Rate/(Stanton Number*Freestream density*(Adiabatic Wall Enthalpy-Wall Enthalpy))
Freestream Velocity = sqrt(2*(Total Specific Enthalpy-Freestream Specific Enthalpy))

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