Profile Drag Coefficient Calculator

✖Skin Friction Drag Force, also known as friction drag, is drag caused by the friction of a fluid against the surface of an object that is moving through it.ⓘ Skin Friction Drag Force [F_skin]			+10% -10%
✖The Pressure Drag Force is caused by the air particles being more compressed on the front-facing surfaces and more spaced out on the back surfaces.ⓘ Pressure Drag Force [D_p]			+10% -10%
✖Free Stream Dynamic Pressure is the kinetic energy per unit volume of fluid at some distance from the body where the density and velocity are freestream values.ⓘ Free Stream Dynamic Pressure [q_∞]			+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%

✖The Profile Drag Coefficient is a dimensionless parameter that describes the viscous effect of the skin friction drag and the pressure drag due to the flow separation on the wing.ⓘ Profile Drag Coefficient [c_d]

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Profile Drag Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Profile Drag Coefficient = (Skin Friction Drag Force+Pressure Drag Force)/(Free Stream Dynamic Pressure*Reference Area)
c_d = (F_skin+D_p)/(q_∞*S)
This formula uses 5 Variables

Variables Used

Profile Drag Coefficient - The Profile Drag Coefficient is a dimensionless parameter that describes the viscous effect of the skin friction drag and the pressure drag due to the flow separation on the wing.
Skin Friction Drag Force - (Measured in Newton) - Skin Friction Drag Force, also known as friction drag, is drag caused by the friction of a fluid against the surface of an object that is moving through it.
Pressure Drag Force - (Measured in Newton) - The Pressure Drag Force is caused by the air particles being more compressed on the front-facing surfaces and more spaced out on the back surfaces.
Free Stream Dynamic Pressure - (Measured in Pascal) - Free Stream Dynamic Pressure is the kinetic energy per unit volume of fluid at some distance from the body where the density and velocity are freestream values.
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.

STEP 1: Convert Input(s) to Base Unit

Skin Friction Drag Force: 100 Newton --> 100 Newton No Conversion Required
Pressure Drag Force: 16 Newton --> 16 Newton No Conversion Required
Free Stream Dynamic Pressure: 450 Pascal --> 450 Pascal No Conversion Required
Reference Area: 5.7 Square Meter --> 5.7 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

c_d = (F_skin+D_p)/(q_∞*S) --> (100+16)/(450*5.7)

Evaluating ... ...

c_d = 0.045224171539961

STEP 3: Convert Result to Output's Unit

0.045224171539961 --> No Conversion Required

FINAL ANSWER

0.045224171539961 ≈ 0.045224 <-- Profile Drag Coefficient

(Calculation completed in 00.004 seconds)

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Shri Govindram Seksaria Institute of Technology and Science (SGSITS), Indore

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< Induced Drag Calculators

Profile Drag Coefficient

LaTeX Go Profile Drag Coefficient = (Skin Friction Drag Force+Pressure Drag Force)/(Free Stream Dynamic Pressure*Reference Area)

Induced Drag Coefficient

LaTeX Go Induced Drag Coefficient = Induced Drag/(Free Stream Dynamic Pressure*Reference Area)

Induced Drag Coefficient given Total Drag Coefficient

LaTeX Go Induced Drag Coefficient = Total Drag Coefficient-Profile Drag Coefficient

Total Drag Coefficient for Subsonic Finite Wing

LaTeX Go Total Drag Coefficient = Profile Drag Coefficient+Induced Drag Coefficient

Profile Drag Coefficient Formula

LaTeX Go

Profile Drag Coefficient = (Skin Friction Drag Force+Pressure Drag Force)/(Free Stream Dynamic Pressure*Reference Area)
c_d = (F_skin+D_p)/(q_∞*S)

How can we reduce profile drag?

Profile drag is reduced through the use of natural laminar flow airfoils, which maintain distinct low-drag ranges (drag buckets) surrounding design lift values. The low-drag ranges can be extended to include off-design values through small flap deflections, similar to cruise flaps.

How to Calculate Profile Drag Coefficient?

Profile Drag Coefficient calculator uses Profile Drag Coefficient = (Skin Friction Drag Force+Pressure Drag Force)/(Free Stream Dynamic Pressure*Reference Area) to calculate the Profile Drag Coefficient, The Profile Drag Coefficient formula calculates the coefficient of the profile drag which is the sum of the skin friction drag and the pressure drag. This formula relates the profile drag coefficient to the profile drag force, which is the drag force acting on the body due to skin friction and pressure differences. Profile Drag Coefficient is denoted by c_d symbol.

How to calculate Profile Drag Coefficient using this online calculator? To use this online calculator for Profile Drag Coefficient, enter Skin Friction Drag Force (F_skin), Pressure Drag Force (D_p), Free Stream Dynamic Pressure (q_∞) & Reference Area (S) and hit the calculate button. Here is how the Profile Drag Coefficient calculation can be explained with given input values -> 0.045224 = (100+16)/(450*5.7).

FAQ

What is Profile Drag Coefficient?

The Profile Drag Coefficient formula calculates the coefficient of the profile drag which is the sum of the skin friction drag and the pressure drag. This formula relates the profile drag coefficient to the profile drag force, which is the drag force acting on the body due to skin friction and pressure differences and is represented as c_d = (F_skin+D_p)/(q_∞*S) or Profile Drag Coefficient = (Skin Friction Drag Force+Pressure Drag Force)/(Free Stream Dynamic Pressure*Reference Area). Skin Friction Drag Force, also known as friction drag, is drag caused by the friction of a fluid against the surface of an object that is moving through it, The Pressure Drag Force is caused by the air particles being more compressed on the front-facing surfaces and more spaced out on the back surfaces, Free Stream Dynamic Pressure is the kinetic energy per unit volume of fluid at some distance from the body where the density and velocity are freestream values & 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.

How to calculate Profile Drag Coefficient?

The Profile Drag Coefficient formula calculates the coefficient of the profile drag which is the sum of the skin friction drag and the pressure drag. This formula relates the profile drag coefficient to the profile drag force, which is the drag force acting on the body due to skin friction and pressure differences is calculated using Profile Drag Coefficient = (Skin Friction Drag Force+Pressure Drag Force)/(Free Stream Dynamic Pressure*Reference Area). To calculate Profile Drag Coefficient, you need Skin Friction Drag Force (F_skin), Pressure Drag Force (D_p), Free Stream Dynamic Pressure (q_∞) & Reference Area (S). With our tool, you need to enter the respective value for Skin Friction Drag Force, Pressure Drag Force, Free Stream Dynamic Pressure & Reference Area and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Profile Drag Coefficient?

In this formula, Profile Drag Coefficient uses Skin Friction Drag Force, Pressure Drag Force, Free Stream Dynamic Pressure & Reference Area. We can use 1 other way(s) to calculate the same, which is/are as follows -

Profile Drag Coefficient = Total Drag Coefficient-Induced Drag Coefficient

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