Drag Force over Flat Plate Calculator

✖Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.ⓘ Freestream Density [ρ_∞]			+10% -10%
✖The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air.ⓘ Freestream Velocity [V_∞]			+10% -10%
✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+10% -10%
✖Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.ⓘ Drag Coefficient [C_D]			+10% -10%

✖Drag Force is the resisting force experienced by an object moving through a fluid.ⓘ Drag Force over Flat Plate [F_D]

⎘ Copy

👎

Formula

Reset

👍

Download Hypersonic Flow Formula PDF PDF Image

Drag Force over Flat Plate Solution

STEP 0: Pre-Calculation Summary

Formula Used

Drag Force = 0.5*Freestream Density*Freestream Velocity^2*Reference Area*Drag Coefficient
F_D = 0.5*ρ_∞*V_∞^2*S*C_D
This formula uses 5 Variables

Variables Used

Drag Force - (Measured in Newton) - Drag Force is the resisting force experienced by an object moving through a fluid.
Freestream Density - (Measured in Kilogram per Cubic Meter) - Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.
Freestream Velocity - (Measured in Meter per Second) - The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
Drag Coefficient - Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.

STEP 1: Convert Input(s) to Base Unit

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
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Drag Coefficient: 2.2 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

F_D = 0.5*ρ_∞*V_∞^2*S*C_D --> 0.5*2.1*100^2*5.08*2.2

Evaluating ... ...

F_D = 117348

STEP 3: Convert Result to Output's Unit

117348 Newton --> No Conversion Required

FINAL ANSWER

117348 Newton <-- Drag Force

(Calculation completed in 00.004 seconds)

You are here -

Home » Engineering » Mechanical » Fluid Mechanics » Hypersonic Flow » Flat Plate for Viscous Flow Case » Approximate Results Applied to Hypersonic Vehicles » Drag Force over Flat Plate

Credits

Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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

Verified by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

Maiarutselvan V has verified this Calculator and 300+ more calculators!

< Approximate Results Applied to Hypersonic Vehicles Calculators

Freestream Velocity over Flat Plate using Stanton Number

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

Freestream Density over Flat Plate using Stanton Number

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

Freestream Stanton Number for Flat Plate

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

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

Drag Force over Flat Plate Formula

Drag Force = 0.5*Freestream Density*Freestream Velocity^2*Reference Area*Drag Coefficient
F_D = 0.5*ρ_∞*V_∞^2*S*C_D

What is drag force?

A drag force is the resistance force caused by the motion of a body through a fluid, such as water or air. A drag force acts opposite to the direction of the oncoming flow velocity.

How to Calculate Drag Force over Flat Plate?

Drag Force over Flat Plate calculator uses Drag Force = 0.5*Freestream Density*Freestream Velocity^2*Reference Area*Drag Coefficient to calculate the Drag Force, Drag Force over Flat Plate formula is defined as a measure of the resistance to motion of a flat plate moving through a fluid, such as air or water, due to the viscous effects of the fluid, which depends on the density and velocity of the fluid, as well as the surface area and drag coefficient of the plate. Drag Force is denoted by F_D symbol.

How to calculate Drag Force over Flat Plate using this online calculator? To use this online calculator for Drag Force over Flat Plate, enter Freestream Density (ρ_∞), Freestream Velocity (V_∞), Reference Area (S) & Drag Coefficient (C_D) and hit the calculate button. Here is how the Drag Force over Flat Plate calculation can be explained with given input values -> 117348 = 0.5*2.1*100^2*5.08*2.2.

FAQ

What is Drag Force over Flat Plate?

Drag Force over Flat Plate formula is defined as a measure of the resistance to motion of a flat plate moving through a fluid, such as air or water, due to the viscous effects of the fluid, which depends on the density and velocity of the fluid, as well as the surface area and drag coefficient of the plate and is represented as F_D = 0.5*ρ_∞*V_∞^2*S*C_D or Drag Force = 0.5*Freestream Density*Freestream Velocity^2*Reference Area*Drag Coefficient. Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area & Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.

How to calculate Drag Force over Flat Plate?

Drag Force over Flat Plate formula is defined as a measure of the resistance to motion of a flat plate moving through a fluid, such as air or water, due to the viscous effects of the fluid, which depends on the density and velocity of the fluid, as well as the surface area and drag coefficient of the plate is calculated using Drag Force = 0.5*Freestream Density*Freestream Velocity^2*Reference Area*Drag Coefficient. To calculate Drag Force over Flat Plate, you need Freestream Density (ρ_∞), Freestream Velocity (V_∞), Reference Area (S) & Drag Coefficient (C_D). With our tool, you need to enter the respective value for Freestream Density, Freestream Velocity, Reference Area & Drag Coefficient 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