With Mecaflux software

1. - Select a profile with drag and lift . For our wing we use the Profile BE50 . (the Polar profiles are already parameterized in MECAFLUX but you can change the Cd and Cl .

2. - Enter parameters of the fluid speed: 10 knots, temperature 20 ° C, density: Air (1225 Kg/m3)

3. - Enter the chord of the profile (the width of the wing, take 4 meter)

4. - Enter the length of the wing (say 10 meters)

5. -Incidence angle of wing (try 10.5 °. The incdences proposed are those studied in wind tunnels .They are confined to the interesting angles)

6. -Click on calculate

The diagram shows the profile BE50 after calculating: 792 Newtons of lift with 10 knot winds

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we seek to balance a weight of 2100 N our lift is too low

1. - Change the profile chord (the width of the wing, take 6 meters)

2. - Change the length of the wing (say 18 meters)

3. -Click on calculate

the lift force for b50 is 2112.604 Newtons (215.485633 Kgf) with 10 knots.

So we need a wing of 18 meters to raise our plane with a speed of 10 knots *****************

see with a speed of 30 knots:

1. - Change the parameters of the fluid speed: 30 knots, temperature 20 ° C, density: Air (1225 Kg/m3)

2. - We keep 18 m height

3. - We keep 6 m in width (chord)

4. -Click on calculate

the lift force for b50 is 19,013.44 Newtons (1939.370426 Kgf) with 30 knots

19013/2112 = 9 times more lift with 3 times more speed

in fact we see, by changing the height and width of the profile, with only a wing of 6 meters in length and 2 meters wide with 30 knots of speed we have a sufficient lift to fly our aircraft.

Warning: the loss of lift at the wing tips are not taken into account.

For a wing with a length of 10 to a width of 1 count approximately 15% loss of lift compared with results MECAFLUX.

For a wing with a length of 10 to a width of 5 count approximately 30% loss of lift compared with results MECAFLUX.

Exemples