Adiabatic Wall Enthalpy over Flat Plate using Stanton Number Calculator

✖The Local Heat Transfer Rate is the measure of heat energy transfer per unit area in hypersonic vehicles, crucial for understanding thermal management and material performance.ⓘ Local Heat Transfer Rate [q_w]			+10% -10%
✖The Freestream Density is the mass per unit volume of air in the flow field surrounding a hypersonic vehicle, crucial for understanding aerodynamic performance.ⓘ Freestream Density [ρ_∞]			+10% -10%
✖The Freestream Velocity is the speed of fluid flow far away from any influence of objects, crucial for analyzing hypersonic vehicle performance and aerodynamic characteristics.ⓘ Freestream Velocity [V_∞]			+10% -10%
✖The Stanton Number is a dimensionless quantity that characterizes the heat transfer between a fluid and a surface, particularly in the context of hypersonic vehicles.ⓘ Stanton Number [St]			+10% -10%
✖The Wall Enthalpy is the measure of energy transfer at the surface of hypersonic vehicles, reflecting the thermal conditions experienced during high-speed flight.ⓘ Wall Enthalpy [h_w]			+10% -10%

✖The Adiabatic Wall Enthalpy is the heat content of a system under adiabatic conditions, relevant for understanding thermal dynamics in hypersonic vehicles.ⓘ Adiabatic Wall Enthalpy over Flat Plate using Stanton Number [h_aw]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Hypersonic Flow Formula PDF PDF Image

Adiabatic Wall Enthalpy over Flat Plate using Stanton Number Solution

STEP 0: Pre-Calculation Summary

Formula Used

Adiabatic Wall Enthalpy = Local Heat Transfer Rate/(Freestream Density*Freestream Velocity*Stanton Number)+Wall Enthalpy
h_aw = q_w/(ρ_∞*V_∞*St)+h_w
This formula uses 6 Variables

Variables Used

Adiabatic Wall Enthalpy - (Measured in Joule per Kilogram) - The Adiabatic Wall Enthalpy is the heat content of a system under adiabatic conditions, relevant for understanding thermal dynamics in hypersonic vehicles.
Local Heat Transfer Rate - (Measured in Watt per Square Meter) - The Local Heat Transfer Rate is the measure of heat energy transfer per unit area in hypersonic vehicles, crucial for understanding thermal management and material performance.
Freestream Density - (Measured in Kilogram per Cubic Meter) - The Freestream Density is the mass per unit volume of air in the flow field surrounding a hypersonic vehicle, crucial for understanding aerodynamic performance.
Freestream Velocity - (Measured in Meter per Second) - The Freestream Velocity is the speed of fluid flow far away from any influence of objects, crucial for analyzing hypersonic vehicle performance and aerodynamic characteristics.
Stanton Number - The Stanton Number is a dimensionless quantity that characterizes the heat transfer between a fluid and a surface, particularly in the context of hypersonic vehicles.
Wall Enthalpy - (Measured in Joule per Kilogram) - The Wall Enthalpy is the measure of energy transfer at the surface of hypersonic vehicles, reflecting the thermal conditions experienced during high-speed flight.

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
Freestream Density: 2.1 Kilogram per Cubic Meter --> 2.1 Kilogram per Cubic Meter No Conversion Required
Freestream Velocity: 100 Meter per Second --> 100 Meter per Second No Conversion Required
Stanton Number: 2 --> 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_∞*V_∞*St)+h_w --> 12000/(2.1*100*2)+99.2

Evaluating ... ...

h_aw = 127.771428571429

STEP 3: Convert Result to Output's Unit

127.771428571429 Joule per Kilogram --> No Conversion Required

FINAL ANSWER

127.771428571429 ≈ 127.7714 Joule per Kilogram <-- Adiabatic Wall Enthalpy

(Calculation completed in 00.020 seconds)

You are here -

Home » Engineering » Mechanical » Fluid Mechanics » Hypersonic Flow » Flat Plate for Viscous Flow Case » Approximate Results Applied to Hypersonic Vehicles » Adiabatic Wall Enthalpy over Flat Plate using Stanton Number

Credits

Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has created this Calculator and 300+ more calculators!

Verified by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

Vinay Mishra has verified this Calculator and 100+ more calculators!

< Approximate Results Applied to Hypersonic Vehicles Calculators

Freestream Velocity over Flat Plate using Stanton Number

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

Freestream Density over Flat Plate using Stanton Number

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

Freestream Stanton Number for Flat Plate

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

Local Heat Transfer over Flat Plate using Stanton Number

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

Adiabatic Wall Enthalpy over Flat Plate using Stanton Number Formula

LaTeX Go

Adiabatic Wall Enthalpy = Local Heat Transfer Rate/(Freestream Density*Freestream Velocity*Stanton Number)+Wall Enthalpy
h_aw = q_w/(ρ_∞*V_∞*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. It is used to characterize heat transfer in forced convection flows.

How to Calculate Adiabatic Wall Enthalpy over Flat Plate using Stanton Number?

Adiabatic Wall Enthalpy over Flat Plate using Stanton Number calculator uses Adiabatic Wall Enthalpy = Local Heat Transfer Rate/(Freestream Density*Freestream Velocity*Stanton Number)+Wall Enthalpy to calculate the Adiabatic Wall Enthalpy, Adiabatic Wall Enthalpy over Flat Plate using Stanton Number formula is defined as a measure of the total enthalpy at the wall of a flat plate in a viscous flow case, which is a critical parameter in understanding heat transfer and fluid flow phenomena in various engineering applications. Adiabatic Wall Enthalpy is denoted by h_aw symbol.

How to calculate Adiabatic Wall Enthalpy over Flat Plate using Stanton Number using this online calculator? To use this online calculator for Adiabatic Wall Enthalpy over Flat Plate using Stanton Number, enter Local Heat Transfer Rate (q_w), Freestream Density (ρ_∞), Freestream Velocity (V_∞), Stanton Number (St) & Wall Enthalpy (h_w) and hit the calculate button. Here is how the Adiabatic Wall Enthalpy over Flat Plate using Stanton Number calculation can be explained with given input values -> 127.7714 = 12000/(2.1*100*2)+99.2.

FAQ

What is Adiabatic Wall Enthalpy over Flat Plate using Stanton Number?

Adiabatic Wall Enthalpy over Flat Plate using Stanton Number formula is defined as a measure of the total enthalpy at the wall of a flat plate in a viscous flow case, which is a critical parameter in understanding heat transfer and fluid flow phenomena in various engineering applications and is represented as h_aw = q_w/(ρ_∞*V_∞*St)+h_w or Adiabatic Wall Enthalpy = Local Heat Transfer Rate/(Freestream Density*Freestream Velocity*Stanton Number)+Wall Enthalpy. The Local Heat Transfer Rate is the measure of heat energy transfer per unit area in hypersonic vehicles, crucial for understanding thermal management and material performance, The Freestream Density is the mass per unit volume of air in the flow field surrounding a hypersonic vehicle, crucial for understanding aerodynamic performance, The Freestream Velocity is the speed of fluid flow far away from any influence of objects, crucial for analyzing hypersonic vehicle performance and aerodynamic characteristics, The Stanton Number is a dimensionless quantity that characterizes the heat transfer between a fluid and a surface, particularly in the context of hypersonic vehicles & The Wall Enthalpy is the measure of energy transfer at the surface of hypersonic vehicles, reflecting the thermal conditions experienced during high-speed flight.

How to calculate Adiabatic Wall Enthalpy over Flat Plate using Stanton Number?

Adiabatic Wall Enthalpy over Flat Plate using Stanton Number formula is defined as a measure of the total enthalpy at the wall of a flat plate in a viscous flow case, which is a critical parameter in understanding heat transfer and fluid flow phenomena in various engineering applications is calculated using Adiabatic Wall Enthalpy = Local Heat Transfer Rate/(Freestream Density*Freestream Velocity*Stanton Number)+Wall Enthalpy. To calculate Adiabatic Wall Enthalpy over Flat Plate using Stanton Number, you need Local Heat Transfer Rate (q_w), Freestream Density (ρ_∞), Freestream Velocity (V_∞), Stanton Number (St) & Wall Enthalpy (h_w). With our tool, you need to enter the respective value for Local Heat Transfer Rate, Freestream Density, Freestream 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.

Home

FREE PDFs

🔍 Search