#Naca airfoil generator matlab series#

The formula for the shape of a NACA 00xx foil, with 'xx' being replaced by the percentage of thickness to chord, is: Plot of a NACA 0015 foil, generated from formula Equation for a symmetrical 4-digit NACA airfoil The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long. The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber.

#Naca airfoil generator matlab series#

Four-digit series airfoils by default have maximum thickness at 30% of the chord (0.3 chords) from the leading edge.

Two digits describing maximum thickness of the airfoil as percent of the chord.Р”Р‡or example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord.

One digit describing the distance of maximum camber from the airfoil leading edge in tens of percent's of the chord.

One digit describing maximum camber as percentage of the chord.

The NACA four-digit wing sections define the profile by:

1.2 Equation for a cambered 4-digit NACA airfoil.1.1 Equation for a symmetrical 4-digit NACA airfoil.I also need to have the N variable in the FSP funcction to be changed to the number of x-y coordinates that are coming in from the airfoil text file. I need to be able to take each of this coordinate and save them in the array x and y variable like I have it in the airfoil5 function. The text file generally contains the name of the airfoil and then the columns of x coordinate and y coordinate. So I need the third option to develop similarly like NACA 5 series and store the data from the text file into the variable x and y. This is an example of NACA 5 series function =Airfoil5(nU,nL,NACA) I need the third option of data collection working similar to that. That is part of the main program that is currently working for 4 and 5 series, it gets the x and y coordinates in an array and plots them for future usage. function =FSP()Р”Р‡printf('Enter option: 1= 4 series, 2=5 series 3= upload') Р”Р‡ourDigit=input(' Type in NACA 4 series: ') Р”Р„lpha = input (' Type in angle of attack in degree: ') Р”Р‡iveDigit= input(' Type in NACA 5 series: ')

However, I want another option to have user generate their own x and y coordinates of the airfoil and I need to be able to use those values in the program. So far: I have generated equation for NACA 4 and 5 series airfoil based on the input series number from the user. I have the main program that is using airfoil geometry to calculate pressure distribution and use the pressure distribution later on in other equations. This is the program I'm trying to create (very new to Matlab).