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Nusselt Number for Hypersonic Vehicle Formula

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The Nusselt Number is the ratio of convective to conductive heat transfer at a boundary in a fluid. Convection includes both advection and diffusion. Check FAQs

N u = \frac{q w \cdot x d}{k \cdot (T wall - Tw)}

N_u - Nusselt Number?q_w - Local Heat Transfer Rate?x_d - Distance from Nose Tip to Required Base Diameter?k - Thermal Conductivity?T_wall - Adiabatic Wall Temperature?Tw - Wall Temperature?

Nusselt Number for Hypersonic Vehicle Example

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Here is how the Nusselt Number for Hypersonic Vehicle equation looks like with Values.

Here is how the Nusselt Number for Hypersonic Vehicle equation looks like with Units.

Here is how the Nusselt Number for Hypersonic Vehicle equation looks like.

1047.2727 = \frac{12000 \cdot 1.2}{0.125 \cdot (125 - 15)}

1047.2727 = \frac{12000W/m² \cdot 1.2m}{0.125W/(m*K) \cdot (125K - 15K)}

1047.2727 = \frac{12000 \cdot 1.2}{0.125 \cdot (125 - 15)}

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Nusselt Number for Hypersonic Vehicle Solution

Follow our step by step solution on how to calculate Nusselt Number for Hypersonic Vehicle?

FIRST Step Consider the formula

N u = \frac{q w \cdot x d}{k \cdot (T wall - Tw)}

Next Step Substitute values of Variables

∴

N u = \frac{12000W/m² \cdot 1.2m}{0.125W/(m*K) \cdot (125K - 15K)}

Next Step Prepare to Evaluate

∴

N u = \frac{12000 \cdot 1.2}{0.125 \cdot (125 - 15)}

Next Step Evaluate

∴

N u = 1047.27272727273

LAST Step Rounding Answer

∴

N u = 1047.2727

Nusselt Number for Hypersonic Vehicle Formula Elements

Variables

Nusselt Number

The Nusselt Number is the ratio of convective to conductive heat transfer at a boundary in a fluid. Convection includes both advection and diffusion.

Symbol: N_u

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Nusselt Number

Local Heat Transfer Rate

Local Heat Transfer Rate, is that energy per second per unit area.

Symbol: q_w

Measurement: Heat Flux DensityUnit: W/m²

Note: Value should be greater than 0.

Formulas to find Local Heat Transfer Rate

Distance from Nose Tip to Required Base Diameter

Distance from Nose Tip to Required Base Diameter, used for studying the leading edge of the hypersonic vehicles.

Symbol: x_d

Measurement: LengthUnit: m

Note: Value can be positive or negative.

Formulas to find Distance from Nose Tip to Required Base Diameter

Thermal Conductivity

Thermal Conductivity is rate of heat passes through specified material, expressed as amount of heat flows per unit time through a unit area with a temperature gradient of one degree per unit distance.

Symbol: k

Measurement: Thermal ConductivityUnit: W/(m*K)

Note: Value should be greater than 0.

Formulas to find Thermal Conductivity

Adiabatic Wall Temperature

Adiabatic wall temperature, is the temperature acquired by a wall in liquid or gas flow if the condition of thermal insulation is observed on it.

Symbol: T_wall

Measurement: TemperatureUnit: K

Note: Value should be greater than 0.

Formulas to find Adiabatic Wall Temperature

Wall Temperature

Wall Temperature is the temperature at the wall.

Symbol: Tw

Measurement: TemperatureUnit: K

Note: Value can be positive or negative.

Formulas to find Wall Temperature

Other formulas in Local Heat Transfer for Hypersonic Flow category

Go Local Heat Transfer Rate using Nusselt's Number

q w = \frac{N u \cdot k \cdot (T wall - Tw)}{x d}

Go Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number

k = \frac{q w \cdot x d}{N u \cdot (T wall - Tw)}

Go Stanton Number for Hypersonic Vehicle

St = \frac{q w}{ρ e \cdot u e \cdot (h aw - h w)}

Go Local Heat Transfer Rate Calculation using Stanton Number

q w = St \cdot ρ e \cdot u e \cdot (h aw - h w)

How to Evaluate Nusselt Number for Hypersonic Vehicle?

Nusselt Number for Hypersonic Vehicle evaluator uses Nusselt Number = (Local Heat Transfer Rate*Distance from Nose Tip to Required Base Diameter)/(Thermal Conductivity*(Adiabatic Wall Temperature-Wall Temperature)) to evaluate the Nusselt Number, Nusselt Number for Hypersonic Vehicle is defined as the ratio of product of local heat-transfer rat and distance along the wall measured from the leading edge to the product of thermal conductivity at the edge of the boundary layer and difference of adiabatic wall temperature and wall temperature. Nusselt Number is denoted by N_u symbol.

How to evaluate Nusselt Number for Hypersonic Vehicle using this online evaluator? To use this online evaluator for Nusselt Number for Hypersonic Vehicle, enter Local Heat Transfer Rate (q_w), Distance from Nose Tip to Required Base Diameter (x_d), Thermal Conductivity (k), Adiabatic Wall Temperature (T_wall) & Wall Temperature (Tw) and hit the calculate button.

FAQs on Nusselt Number for Hypersonic Vehicle

What is the formula to find Nusselt Number for Hypersonic Vehicle?

The formula of Nusselt Number for Hypersonic Vehicle is expressed as Nusselt Number = (Local Heat Transfer Rate*Distance from Nose Tip to Required Base Diameter)/(Thermal Conductivity*(Adiabatic Wall Temperature-Wall Temperature)). Here is an example- 1047.273 = (12000*1.2)/(0.125*(125-15)).

How to calculate Nusselt Number for Hypersonic Vehicle?

With Local Heat Transfer Rate (q_w), Distance from Nose Tip to Required Base Diameter (x_d), Thermal Conductivity (k), Adiabatic Wall Temperature (T_wall) & Wall Temperature (Tw) we can find Nusselt Number for Hypersonic Vehicle using the formula - Nusselt Number = (Local Heat Transfer Rate*Distance from Nose Tip to Required Base Diameter)/(Thermal Conductivity*(Adiabatic Wall Temperature-Wall Temperature)).

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Nusselt Number for Hypersonic Vehicle Formula

Nusselt Number for Hypersonic Vehicle Example

Nusselt Number for Hypersonic Vehicle Solution

Nusselt Number for Hypersonic Vehicle Formula Elements

Other formulas in Local Heat Transfer for Hypersonic Flow category

How to Evaluate Nusselt Number for Hypersonic Vehicle?

FAQs on Nusselt Number for Hypersonic Vehicle

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