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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
FINAL ANSWER
0.104999999999998 Meter <-- Half Thickness
(Calculation completed in 00.000 seconds)

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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.
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