Adiabatic Wall Enthalpy using Stanton Number 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 Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow.ⓘ Stanton Number [St]			+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 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 using Stanton Number [h_aw]

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Adiabatic Wall Enthalpy using Stanton Number Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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.
Stanton Number - The Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow.
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
Stanton Number: 0.4 --> 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

h_aw = q_w/(ρ_e*u_e*St)+h_w --> 12000/(1200*8.8*0.4)+99.2

Evaluating ... ...

h_aw = 102.040909090909

STEP 3: Convert Result to Output's Unit

102.040909090909 Joule per Kilogram --> No Conversion Required

FINAL ANSWER

102.040909090909 ≈ 102.0409 Joule per Kilogram <-- Adiabatic Wall Enthalpy

(Calculation completed in 00.004 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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Indian Institute of Technology (IIT), Bombay

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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))

Adiabatic Wall Enthalpy using Stanton Number Formula

LaTeX Go

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

How to Calculate Adiabatic Wall Enthalpy using Stanton Number?

Adiabatic Wall Enthalpy using Stanton Number calculator uses Adiabatic Wall Enthalpy = Local Heat Transfer Rate/(Static Density*Static Velocity*Stanton Number)+Wall Enthalpy to calculate the Adiabatic Wall Enthalpy, Adiabatic Wall Enthalpy using Stanton Number formula is defined as a measure of the total heat transfer between the wall and the fluid in a hypersonic flow, which is a critical parameter in understanding the heat shield design and thermal protection of spacecraft during re-entry into the Earth's atmosphere. Adiabatic Wall Enthalpy is denoted by h_aw symbol.

How to calculate Adiabatic Wall Enthalpy using Stanton Number using this online calculator? To use this online calculator for Adiabatic Wall Enthalpy using Stanton Number, enter Local Heat Transfer Rate (q_w), Static Density (ρ_e), Static Velocity (u_e), Stanton Number (St) & Wall Enthalpy (h_w) and hit the calculate button. Here is how the Adiabatic Wall Enthalpy using Stanton Number calculation can be explained with given input values -> 102.0409 = 12000/(1200*8.8*0.4)+99.2.

FAQ

What is Adiabatic Wall Enthalpy using Stanton Number?

Adiabatic Wall Enthalpy using Stanton Number formula is defined as a measure of the total heat transfer between the wall and the fluid in a hypersonic flow, which is a critical parameter in understanding the heat shield design and thermal protection of spacecraft during re-entry into the Earth's atmosphere and is represented as h_aw = q_w/(ρ_e*u_e*St)+h_w or Adiabatic Wall Enthalpy = Local Heat Transfer Rate/(Static Density*Static Velocity*Stanton Number)+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 Stanton Number is a dimensionless quantity used to characterize heat transfer and frictional drag in the boundary layer of hypersonic flow & 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 Adiabatic Wall Enthalpy using Stanton Number?

Adiabatic Wall Enthalpy using Stanton Number formula is defined as a measure of the total heat transfer between the wall and the fluid in a hypersonic flow, which is a critical parameter in understanding the heat shield design and thermal protection of spacecraft during re-entry into the Earth's atmosphere is calculated using Adiabatic Wall Enthalpy = Local Heat Transfer Rate/(Static Density*Static Velocity*Stanton Number)+Wall Enthalpy. To calculate Adiabatic Wall Enthalpy using Stanton Number, you need Local Heat Transfer Rate (q_w), Static Density (ρ_e), Static Velocity (u_e), Stanton Number (St) & Wall Enthalpy (h_w). With our tool, you need to enter the respective value for Local Heat Transfer Rate, Static Density, Static Velocity, Stanton Number & 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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