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Stanton Number for Hypersonic Vehicle Formula

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The Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow. Check FAQs

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

St - Stanton Number?q_w - Local Heat Transfer Rate?ρ_e - Static Density?u_e - Static Velocity?h_aw - Adiabatic Wall Enthalpy?h_w - Wall Enthalpy?

Stanton Number for Hypersonic Vehicle Example

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

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

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

0.4058 = \frac{12000}{1200 \cdot 8.8 \cdot (102 - 99.2)}

0.4058 = \frac{12000W/m²}{1200kg/m³ \cdot 8.8m/s \cdot (102J/kg - 99.2J/kg)}

0.4058 = \frac{12000}{1200 \cdot 8.8 \cdot (102 - 99.2)}

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Stanton Number for Hypersonic Vehicle Solution

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

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

St = \frac{12000W/m²}{1200kg/m³ \cdot 8.8m/s \cdot (102J/kg - 99.2J/kg)}

Next Step Prepare to Evaluate

∴

St = \frac{12000}{1200 \cdot 8.8 \cdot (102 - 99.2)}

Next Step Evaluate

∴

St = 0.405844155844156

LAST Step Rounding Answer

∴

St = 0.4058

Stanton Number for Hypersonic Vehicle Formula Elements

Variables

Stanton Number

The Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow.

Symbol: St

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Stanton Number

Open Variable

Local Heat Transfer Rate

The Local Heat Transfer Rate is the amount of heat transferred per unit area per unit time from the surface to the fluid in a hypersonic boundary layer.

Symbol: q_w

Measurement: Heat Flux DensityUnit: W/m²

Note: Value should be greater than 0.

Formulas to find Local Heat Transfer Rate

Open Variable

Static Density

The Static Density is the density of air at a given altitude and temperature, used to model the boundary layer in hypersonic flow conditions.

Symbol: ρ_e

Measurement: DensityUnit: kg/m³

Note: Value should be greater than 0.

Formulas to find Static Density

Open Variable

Static Velocity

The Static Velocity is the velocity of the fluid in the boundary layer at a given point, describing the flow characteristics near the surface.

Symbol: u_e

Measurement: SpeedUnit: m/s

Note: Value should be greater than 0.

Formulas to find Static Velocity

Open Variable

Adiabatic Wall Enthalpy

The Adiabatic Wall Enthalpy is the total enthalpy of a gas at the wall of a hypersonic vehicle, considering the heat transfer and friction effects.

Symbol: h_aw

Measurement: Specific EnergyUnit: J/kg

Note: Value should be greater than 0.

Formulas to find Adiabatic Wall Enthalpy

Open Variable

Wall Enthalpy

The Wall Enthalpy is the total heat content of the wall boundary layer in a hypersonic flow, including both sensible and latent heat components.

Symbol: h_w

Measurement: Specific EnergyUnit: J/kg

Note: Value should be greater than 0.

Formulas to find Wall Enthalpy

Open Variable

Other formulas in Local Heat Transfer for Hypersonic Flow category

Go Nusselt Number for Hypersonic Vehicle

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

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 Local Heat Transfer Rate Calculation using Stanton Number

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

See More

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How to Evaluate Stanton Number for Hypersonic Vehicle?

Stanton Number for Hypersonic Vehicle evaluator uses Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)) to evaluate the Stanton Number, Stanton Number for Hypersonic Vehicle formula is defined as a dimensionless quantity used to characterize the heat transfer between the wall and the fluid in a hypersonic flow, providing a measure of the heat flux at the wall relative to the total enthalpy difference between the wall and the edge of the boundary layer. Stanton Number is denoted by St symbol.

How to evaluate Stanton Number for Hypersonic Vehicle using this online evaluator? To use this online evaluator for Stanton Number for Hypersonic Vehicle, enter Local Heat Transfer Rate (q_w), Static Density (ρ_e), Static Velocity (u_e), Adiabatic Wall Enthalpy (h_aw) & Wall Enthalpy (h_w) and hit the calculate button.

FAQs on Stanton Number for Hypersonic Vehicle

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

The formula of Stanton Number for Hypersonic Vehicle is expressed as Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)). Here is an example- 0.405844 = 12000/(1200*8.8*(102-99.2)).

How to calculate Stanton Number for Hypersonic Vehicle?

With Local Heat Transfer Rate (q_w), Static Density (ρ_e), Static Velocity (u_e), Adiabatic Wall Enthalpy (h_aw) & Wall Enthalpy (h_w) we can find Stanton Number for Hypersonic Vehicle using the formula - Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)).

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