## Credits

Sri sivasubramaniyanadar college of engineering (ssn college of engineering), Chennai
Prasana Kannan has created this Calculator and 25+ more calculators!
Mahatma Gandhi Institute of Technology (MGIT), Hyderabad
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## Aerofoil Thickness For 4 Digit Series Solution

STEP 0: Pre-Calculation Summary
Formula Used
Half Thickness = (Maximum Thickness* ((0.2969*((Position Along The chord)^(0.5)))- (0.1260*Position Along The chord)- (0.3516*((Position Along The chord)^(2)))+ (0.2843*((Position Along The chord)^(3)))- (0.1015*((Position Along The chord)^(4)))))/0.2
yt(x) = (t* ((0.2969*((x)^(0.5)))- (0.1260*x)- (0.3516*((x)^(2)))+ (0.2843*((x)^(3)))- (0.1015*((x)^(4)))))/0.2
This formula uses 2 Variables
Variables Used
Maximum Thickness - Maximum Thickness is the fraction of the chord length. (Measured in Meter)
Position Along The chord- Position Along The chord is the distance between the trailing edge and the point where the chord intersects the leading edge.
STEP 1: Convert Input(s) to Base Unit
Maximum Thickness: 10 Meter --> 10 Meter No Conversion Required
Position Along The chord: 1 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
yt(x) = (t* ((0.2969*((x)^(0.5)))- (0.1260*x)- (0.3516*((x)^(2)))+ (0.2843*((x)^(3)))- (0.1015*((x)^(4)))))/0.2 --> (10* ((0.2969*((1)^(0.5)))- (0.1260*1)- (0.3516*((1)^(2)))+ (0.2843*((1)^(3)))- (0.1015*((1)^(4)))))/0.2
Evaluating ... ...
yt(x) = 0.104999999999998
STEP 3: Convert Result to Output's Unit
0.104999999999998 Meter --> No Conversion Required
0.104999999999998 Meter <-- Half Thickness
(Calculation completed in 00.000 seconds)

## < 10+ Aircraft Conceptual Design Calculators

Summations of priorities of objectives that need to be maximized (Millitary planes)
Priority Sum of objectives to be maximized (%) = Performance Priority (%)+Flight Quality Priority (%)+Scariness Priority (%)+Maintainability Priority (%)+Producibility Priority (%)+Disposability Priority (%)+Stealth Priority (%) Go
Weight Priority (%) = ((Minimum Design Index*100)-(Cost Index*Cost Priority (%))-(Period Index*Period Priority (%)))/Weight Index Go
Cost Priority (%) = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Period Index*Period Priority (%)))/Cost Index Go
Period Priority (%) = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Cost Index*Cost Priority (%)))/Period Index Go
Period Index = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Cost Index*Cost Priority (%)))/Period Priority (%) Go
Weight Index = ((Minimum Design Index*100)-(Cost Index*Cost Priority (%))-(Period Index*Period Priority (%)))/Weight Priority (%) Go
Cost Index = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Period Index*Period Priority (%)))/Cost Priority (%) Go
Minimum Design Index = ((Cost Index*Cost Priority (%))+(Weight Index*Weight Priority (%))+(Period Index*Period Priority (%)))/100 Go
Summation of priorities of all objectives that need to be minimized
Priority Sum of objectives to be minimized(%) = Cost Priority (%)+Weight Priority (%)+Period Priority (%) Go
Propulsion Net Thrust
Thrust force = Air mass flow rate*(Velocity of Jet-Flight velocity) Go

### Aerofoil Thickness For 4 Digit Series Formula

Half Thickness = (Maximum Thickness* ((0.2969*((Position Along The chord)^(0.5)))- (0.1260*Position Along The chord)- (0.3516*((Position Along The chord)^(2)))+ (0.2843*((Position Along The chord)^(3)))- (0.1015*((Position Along The chord)^(4)))))/0.2
yt(x) = (t* ((0.2969*((x)^(0.5)))- (0.1260*x)- (0.3516*((x)^(2)))+ (0.2843*((x)^(3)))- (0.1015*((x)^(4)))))/0.2

## Does thickness of airfoil affect lift?

Increasing the thickness will increase the lift. Increasing the area will increase the lift. Increasing the altitude will decrease the lift.

## How to Calculate Aerofoil Thickness For 4 Digit Series?

Aerofoil Thickness For 4 Digit Series calculator uses Half Thickness = (Maximum Thickness* ((0.2969*((Position Along The chord)^(0.5)))- (0.1260*Position Along The chord)- (0.3516*((Position Along The chord)^(2)))+ (0.2843*((Position Along The chord)^(3)))- (0.1015*((Position Along The chord)^(4)))))/0.2 to calculate the Half Thickness, The Aerofoil Thickness For 4 Digit Series formula is the half-thickness of the aerofoil at a distance of x from the leading edge, which is to be accounted for twice in consideration for wing design. Half Thickness is denoted by yt(x) symbol.

How to calculate Aerofoil Thickness For 4 Digit Series using this online calculator? To use this online calculator for Aerofoil Thickness For 4 Digit Series, enter Maximum Thickness (t) & Position Along The chord (x) and hit the calculate button. Here is how the Aerofoil Thickness For 4 Digit Series calculation can be explained with given input values -> 0.105 = (10* ((0.2969*((1)^(0.5)))- (0.1260*1)- (0.3516*((1)^(2)))+ (0.2843*((1)^(3)))- (0.1015*((1)^(4)))))/0.2 .

### FAQ

What is Aerofoil Thickness For 4 Digit Series?
The Aerofoil Thickness For 4 Digit Series formula is the half-thickness of the aerofoil at a distance of x from the leading edge, which is to be accounted for twice in consideration for wing design and is represented as yt(x) = (t* ((0.2969*((x)^(0.5)))- (0.1260*x)- (0.3516*((x)^(2)))+ (0.2843*((x)^(3)))- (0.1015*((x)^(4)))))/0.2 or Half Thickness = (Maximum Thickness* ((0.2969*((Position Along The chord)^(0.5)))- (0.1260*Position Along The chord)- (0.3516*((Position Along The chord)^(2)))+ (0.2843*((Position Along The chord)^(3)))- (0.1015*((Position Along The chord)^(4)))))/0.2 . Maximum Thickness is the fraction of the chord length & Position Along The chord is the distance between the trailing edge and the point where the chord intersects the leading edge.
How to calculate Aerofoil Thickness For 4 Digit Series?
The Aerofoil Thickness For 4 Digit Series formula is the half-thickness of the aerofoil at a distance of x from the leading edge, which is to be accounted for twice in consideration for wing design is calculated using Half Thickness = (Maximum Thickness* ((0.2969*((Position Along The chord)^(0.5)))- (0.1260*Position Along The chord)- (0.3516*((Position Along The chord)^(2)))+ (0.2843*((Position Along The chord)^(3)))- (0.1015*((Position Along The chord)^(4)))))/0.2 . To calculate Aerofoil Thickness For 4 Digit Series, you need Maximum Thickness (t) & Position Along The chord (x). With our tool, you need to enter the respective value for Maximum Thickness & Position Along The chord and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well. Let Others Know