Coefficient of Drag over Flat under Freestream Flow Conditions Calculator

✖The Drag Force is the resistance experienced by an object moving through a fluid, significantly impacting the performance and stability of hypersonic vehicles.ⓘ Drag Force [F_D]			+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 Reference Area is the projected area of a hypersonic vehicle that is used for aerodynamic analysis and performance evaluation in flight.ⓘ Reference Area [S]			+10% -10%

✖The Drag Coefficient is a dimensionless number that quantifies the drag or resistance of an object in a fluid environment, specifically for hypersonic vehicles.ⓘ Coefficient of Drag over Flat under Freestream Flow Conditions [C_D]

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Coefficient of Drag over Flat under Freestream Flow Conditions Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

Drag Coefficient - The Drag Coefficient is a dimensionless number that quantifies the drag or resistance of an object in a fluid environment, specifically for hypersonic vehicles.
Drag Force - (Measured in Newton) - The Drag Force is the resistance experienced by an object moving through a fluid, significantly impacting the performance and stability of hypersonic vehicles.
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.
Reference Area - (Measured in Square Meter) - The Reference Area is the projected area of a hypersonic vehicle that is used for aerodynamic analysis and performance evaluation in flight.

STEP 1: Convert Input(s) to Base Unit

Drag Force: 81.98358 Newton --> 81.98358 Newton 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
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_D = F_D/(0.5*ρ_∞*V_∞^2*S) --> 81.98358/(0.5*2.1*100^2*5.08)

Evaluating ... ...

C_D = 0.001537

STEP 3: Convert Result to Output's Unit

0.001537 --> No Conversion Required

FINAL ANSWER

0.001537 <-- Drag Coefficient

(Calculation completed in 00.004 seconds)

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Amrita School of Engineering (ASE), Vallikavu

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< 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)

Coefficient of Drag over Flat under Freestream Flow Conditions Formula

LaTeX Go

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

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 Coefficient of Drag over Flat under Freestream Flow Conditions?

Coefficient of Drag over Flat under Freestream Flow Conditions calculator uses Drag Coefficient = Drag Force/(0.5*Freestream Density*Freestream Velocity^2*Reference Area) to calculate the Drag Coefficient, Coefficient of Drag over Flat under Freestream Flow Conditions formula is defined as a dimensionless quantity that characterizes the drag forces experienced by a flat plate in a viscous flow, providing a measure of the resistance to motion in a fluid. Drag Coefficient is denoted by C_D symbol.

How to calculate Coefficient of Drag over Flat under Freestream Flow Conditions using this online calculator? To use this online calculator for Coefficient of Drag over Flat under Freestream Flow Conditions, enter Drag Force (F_D), Freestream Density (ρ_∞), Freestream Velocity (V_∞) & Reference Area (S) and hit the calculate button. Here is how the Coefficient of Drag over Flat under Freestream Flow Conditions calculation can be explained with given input values -> 0.001537 = 81.98358/(0.5*2.1*100^2*5.08).

FAQ

What is Coefficient of Drag over Flat under Freestream Flow Conditions?

Coefficient of Drag over Flat under Freestream Flow Conditions formula is defined as a dimensionless quantity that characterizes the drag forces experienced by a flat plate in a viscous flow, providing a measure of the resistance to motion in a fluid and is represented as C_D = F_D/(0.5*ρ_∞*V_∞^2*S) or Drag Coefficient = Drag Force/(0.5*Freestream Density*Freestream Velocity^2*Reference Area). The Drag Force is the resistance experienced by an object moving through a fluid, significantly impacting the performance and stability of hypersonic vehicles, 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 Reference Area is the projected area of a hypersonic vehicle that is used for aerodynamic analysis and performance evaluation in flight.

How to calculate Coefficient of Drag over Flat under Freestream Flow Conditions?

Coefficient of Drag over Flat under Freestream Flow Conditions formula is defined as a dimensionless quantity that characterizes the drag forces experienced by a flat plate in a viscous flow, providing a measure of the resistance to motion in a fluid is calculated using Drag Coefficient = Drag Force/(0.5*Freestream Density*Freestream Velocity^2*Reference Area). To calculate Coefficient of Drag over Flat under Freestream Flow Conditions, you need Drag Force (F_D), Freestream Density (ρ_∞), Freestream Velocity (V_∞) & Reference Area (S). With our tool, you need to enter the respective value for Drag Force, Freestream Density, Freestream Velocity & Reference Area 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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