Stanton Number for Hypersonic Vehicle Calculator

✖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.ⓘ Local Heat Transfer Rate [q_w]			+10% -10%
✖The Static Density is the density of air at a given altitude and temperature, used to model the boundary layer in hypersonic flow conditions.ⓘ Static Density [ρ_e]			+10% -10%
✖The Static Velocity is the velocity of the fluid in the boundary layer at a given point, describing the flow characteristics near the surface.ⓘ Static Velocity [u_e]			+10% -10%
✖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.ⓘ Adiabatic Wall Enthalpy [h_aw]			+10% -10%
✖The Wall Enthalpy is the total heat content of the wall boundary layer in a hypersonic flow, including both sensible and latent heat components.ⓘ Wall Enthalpy [h_w]			+10% -10%

✖The Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow.ⓘ Stanton Number for Hypersonic Vehicle [St]

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Stanton Number for Hypersonic Vehicle Solution

STEP 0: Pre-Calculation Summary

Formula Used

Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))
St = q_w/(ρ_e*u_e*(h_aw-h_w))
This formula uses 6 Variables

Variables Used

Stanton Number - The Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow.
Local Heat Transfer Rate - (Measured in Watt per Square Meter) - 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.
Static Density - (Measured in Kilogram per Cubic Meter) - The Static Density is the density of air at a given altitude and temperature, used to model the boundary layer in hypersonic flow conditions.
Static Velocity - (Measured in Meter per Second) - The Static Velocity is the velocity of the fluid in the boundary layer at a given point, describing the flow characteristics near the surface.
Adiabatic Wall Enthalpy - (Measured in Joule per Kilogram) - 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.
Wall Enthalpy - (Measured in Joule per Kilogram) - The Wall Enthalpy is the total heat content of the wall boundary layer in a hypersonic flow, including both sensible and latent heat components.

STEP 1: Convert Input(s) to Base Unit

Local Heat Transfer Rate: 12000 Watt per Square Meter --> 12000 Watt per Square Meter No Conversion Required
Static Density: 1200 Kilogram per Cubic Meter --> 1200 Kilogram per Cubic Meter No Conversion Required
Static Velocity: 8.8 Meter per Second --> 8.8 Meter per Second No Conversion Required
Adiabatic Wall Enthalpy: 102 Joule per Kilogram --> 102 Joule per Kilogram No Conversion Required
Wall Enthalpy: 99.2 Joule per Kilogram --> 99.2 Joule per Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

St = q_w/(ρ_e*u_e*(h_aw-h_w)) --> 12000/(1200*8.8*(102-99.2))

Evaluating ... ...

St = 0.405844155844156

STEP 3: Convert Result to Output's Unit

0.405844155844156 --> No Conversion Required

FINAL ANSWER

0.405844155844156 ≈ 0.405844 <-- Stanton Number

(Calculation completed in 00.004 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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PSG College of Technology (PSGCT), Coimbatore

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< Local Heat Transfer for Hypersonic Flow Calculators

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

LaTeX Go Thermal Conductivity = (Local Heat Transfer Rate*Distance from Nose Tip to Required Base Diameter)/(Nusselt Number*(Adiabatic Wall Temperature-Wall Temperature))

Local Heat Transfer Rate using Nusselt's Number

LaTeX Go Local Heat Transfer Rate = (Nusselt Number*Thermal Conductivity*(Adiabatic Wall Temperature-Wall Temperature))/(Distance from Nose Tip to Required Base Diameter)

Nusselt Number for Hypersonic Vehicle

LaTeX Go Nusselt Number = (Local Heat Transfer Rate*Distance from Nose Tip to Required Base Diameter)/(Thermal Conductivity*(Adiabatic Wall Temperature-Wall Temperature))

Stanton Number for Hypersonic Vehicle

LaTeX Go Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))

Stanton Number for Hypersonic Vehicle Formula

LaTeX Go

Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy))
St = q_w/(ρ_e*u_e*(h_aw-h_w))

What is Stanton number?

The Stanton number, St, is a dimensionless number that measures the ratio of heat transferred into a fluid to the thermal capacity of the fluid.

How to Calculate Stanton Number for Hypersonic Vehicle?

Stanton Number for Hypersonic Vehicle calculator uses Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)) to calculate 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 calculate Stanton Number for Hypersonic Vehicle using this online calculator? To use this online calculator 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. Here is how the Stanton Number for Hypersonic Vehicle calculation can be explained with given input values -> 0.405844 = 12000/(1200*8.8*(102-99.2)).

FAQ

What is Stanton Number for Hypersonic Vehicle?

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 and is represented as St = q_w/(ρ_e*u_e*(h_aw-h_w)) or Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)). 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, The Static Density is the density of air at a given altitude and temperature, used to model the boundary layer in hypersonic flow conditions, The Static Velocity is the velocity of the fluid in the boundary layer at a given point, describing the flow characteristics near the surface, 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 & The Wall Enthalpy is the total heat content of the wall boundary layer in a hypersonic flow, including both sensible and latent heat components.

How to calculate Stanton Number for Hypersonic Vehicle?

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 is calculated using Stanton Number = Local Heat Transfer Rate/(Static Density*Static Velocity*(Adiabatic Wall Enthalpy-Wall Enthalpy)). To calculate Stanton Number for Hypersonic Vehicle, you need Local Heat Transfer Rate (q_w), Static Density (ρ_e), Static Velocity (u_e), Adiabatic Wall Enthalpy (h_aw) & Wall Enthalpy (h_w). With our tool, you need to enter the respective value for Local Heat Transfer Rate, Static Density, Static Velocity, Adiabatic Wall Enthalpy & Wall Enthalpy and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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