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The wing planform is done. Now do I add the wing chord to the root and tip chords?

inaamh
Contributor

The wing planform is done. Now do I add the wing chord to the root and tip chords?

inaamh
Contributor
Contributor

The wing planform is done. Now do I add the wing chord to the root and tip chords?

 

This is the aerofoil I am adding to the root and tip chords, it's reversed and flipped in the x-axis, because it's original look is backwards.  But how do I add the airfoils in and how do I close the gap between the last two points of the trailing edge in this aerofoil?

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inaamh
Contributor
Contributor

These are my aerofoil coordinates:

-1-0.0104
-0.99-0.0071
-0.98-0.0039
-0.97-0.0009
-0.950.0049
-0.920.0131
-0.90.0181
-0.870.0251
-0.850.0294
-0.820.0353
-0.80.0389
-0.770.0439
-0.750.0469
-0.720.0509
-0.70.0533
-0.680.0555
-0.650.0585
-0.620.061
-0.60.0625
-0.570.0645
-0.550.0656
-0.530.0666
-0.50.0678
-0.480.0684
-0.450.0692
-0.430.0695
-0.40.0697
-0.380.0698
-0.350.0696
-0.330.0692
-0.30.0685
-0.270.0673
-0.250.0664
-0.220.0646
-0.20.0632
-0.170.0606
-0.150.0585
-0.120.0548
-0.10.0518
-0.070.0462
-0.050.0411
-0.040.0381
-0.030.0343
-0.020.0293
-0.010.0219
-0.0050.0158
-0.0020.0095
00
-0.002-0.0093
-0.005-0.016
-0.01-0.0221
-0.02-0.0295
-0.03-0.0344
-0.04-0.0381
-0.05-0.0412
-0.07-0.0462
-0.1-0.0517
-0.12-0.0547
-0.15-0.0585
-0.17-0.0606
-0.2-0.0633
-0.22-0.0647
-0.25-0.0666
-0.28-0.068
-0.3-0.0687
-0.32-0.0692
-0.35-0.0696
-0.37-0.0696
-0.4-0.0692
-0.42-0.0688
-0.45-0.0676
-0.48-0.0657
-0.5-0.0644
-0.53-0.0614
-0.55-0.0588
-0.58-0.0543
-0.6-0.0509
-0.63-0.0451
-0.65-0.041
-0.68-0.0346
-0.7-0.0302
-0.73-0.0235
-0.75-0.0192
-0.77-0.015
-0.8-0.0093
-0.83-0.0048
-0.85-0.0024
-0.87-0.0013
-0.89-0.0008
-0.92-0.0016
-0.94-0.0035
-0.95-0.0049
-0.96-0.0066
-0.97-0.0085
-0.98-0.0109
-0.99-0.0137
-1-0.0163
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