AIRFOIL SHARK NOSE MODIFICATION  MANUAL
Fortran version
Version 0.1 20260802

- Put your standard airfoil.dat file in the working directory (you must use exactly these name airfoil.dat)
- Edit asndata.txt to select shark nose parameters
- Run ./asn.out executable in Linux (or asn.exe in Windows)
- Result file airfoil-sn.dat
- Result file airfoil-sn.dxf

File asndata.txt structure:

real1	real2	real3
real4
real5	real6	real7
real8

Example:

3.0	1.0 1.3
6.0
16.0	1.0 1.3
1.0

Explanation:

Line 1 column 1: real1 (0 to 100 is % of chord first shark nose mofification fron 0% to real1)
Line 1 column 2: real2 (0.0 to 5.0 is % of maximum modification deflection using a generic parabola of the type k1*x^n1
Line 1 column 3: real3 (0.0 to 5.0 is exponent n1 of the generic parabola modification

Line 2 column 1: real4 (end of shark nose inlet in %, init of shark nose inlet is real1)

Line 3 column 1: real5 (0 to 100 is % of chord second shark nose mofification from real1 to real5)
Line 3 column 2: real6 (0.0 to 5.0 usual values is % of maximum modification deflection using a generic parabola of the type k3*(x3-x)^n3
Line 3 column 3: real7 (0.0 to 5.0 usual values is exponent n3 of the generic parabola modification

Line 4: real8 thickness amplification (1.0 is most habitual)

Program generates also airfoil-sn.dxf file for viewing in CAD.

Run:

Windows64:

asn-win64.exe (double click)

Linux64: ./asn-lin64.out


