.: code Airfoil Editor

Allows modifying geometry of an initial airfoil and at the same time inspecting pressure distribution based on set of conditions : Mach, Re, Alpha.

The code works in two regimes:

  1. Modification of upper and lower surface.
  2. Modification of thickness and camber.

The graphical user interface is based on MS VisualBasic.
Use "." as decimal separator on Windows platforms.

.: format of initial geometry:

  • Format (see. example on the bottom of page) upper surface coordinates are specified from leading to trailing edge first, then lower surface coordinates follow in the same order.

    1. NU - number of points on upper surface
    2. NL - number of points on lower surface
    3. XU - x-coordinate of upper surface
    4. YU - y-coordinate of upper surface
    5. XL - x-coordinate of lower surface
    6. YL - y-coordinate of lower surface

.: panel Input file:

Input File Choice of initial file
Output File The name of output file with calculation result
Input Input of initial file
View Foil Visualization of foil geometry
UL Edit upper and lower surfaces
TC Edit thickness and camber
Geometry Edit Switch to editing panel

.: foil geometry:

mu number of coordinates on upper surface
ml number of coordinates on lower surface
Mach Mach number
To stagnation temperature
Tref temperature at infinity
Re number Reynolds number
Lref reference length
Sref reference wing area
Angle of attack angle of attack

.: Edit panel for thickness T(x) and camber C(x):

Lift coef. lift coefficient
Drag coef. drag coefficient (integral of Cp)
Max thickness maximum thickness
Max th. pos. x-coordinate of maximum thickness
Mach Mach number
Alpha angle of attack
Alpha, Cliftchoice of Cp calculation mode: with specified Clift or alpha
Thickness, Camber choice of parameter to edit
Right mouse click on the graph or panels "Thickness", "Camber"
defines editing knot,
the chosen knot becomes red
Movement of the pressed left key of the mouse on the graph displaces the corresponding knot
Checkboxes under X Y define degrees of freedom for each knot

Editing parametres are five co-ordinates of broken two-unit curve Bezier. This curve actually depends from 10 parameters (X, Y for each knot) and defines displacement of the edited parameter: a thickness or an camber from initial distribution

.: Ср distribution:

Black line Cp distribution on initial shape
Blue line Cp distribution on modified shape

.: Edit panel for U(x) and L(x):

Lift coef. lift coefficient
Drag coef. drag coefficient (integral of Cp)
Max thickness maximum thickness
Max th. pos. x-coordinate of maximum thickness
Mach Mach number
Alpha angle of attack
Alpha, Cliftchoice of Cp calculation mode: with specified Clift or alpha
Upper S, Lower S choice of parameter to edit
Right mouse click on the graph or panels "Upper S", "Lower S"
activates knot to be edited,
the active knot becomes red
Mouse movement with left button depressed displaces the active knot
Checkboxes under X Y define degrees of freedom for each knot

Editing parameters are five co-ordinates of broken two-unit Bezier curve. This curve actually depends from 10 parameters (X, Y for each knot) and defines displacements of edited values (upper and lower surfaces) from initial distribution.

.: Ср distribution:

Black line Cp distribution on initial shape
Blue line Cp distribution on modified shape

.: Example of the input data file:

RAE-2822
YSYM NU NL
0.00000 29.00000 29.00000
XU YU
0.000000 0.000000
0.00250.012586
0.005 0.017608
0.00750.021279
0.01250.026723
0.025 0.035517
0.050.045757
0.075 0.052420
0.1 0.057471
0.125 0.061525
0.15 0.064844
0.20 0.069794
0.25 0.072976
0.30 0.074746
0.35 0.075323
0.40 0.074853
0.45 0.073437
0.50 0.071141
0.55 0.068005
0.60 0.064045
0.65 0.059252
0.70 0.053598
0.75 0.047038
0.80 0.039522
0.85 0.031014
0.90 0.021540
0.95 0.011391
0.97 0.007432
1.000000 0.000935
XL YL
0.000000 0.000000
0.0025 -0.011854
0.005-0.016411
0.0075 -0.019759
0.0125 -0.024802
0.025-0.033260
0.05 -0.043695
0.075-0.050785
0.1 -0.056273
0.125-0.060738
0.15 -0.064417
0.20 -0.069838
0.25 -0.073095
0.30 -0.074585
0.35 -0.074572
0.40 -0.073142
0.45 -0.070275
0.50 -0.065941
0.55 -0.060149
0.60 -0.052969
0.65 -0.044568
0.70 -0.035236
0.75 -0.025467
0.80 -0.016055
0.85 -0.008106
0.90 -0.002637
0.95 -0.000166
0.97 -0.000047
1.000000 -0.000935