GM15 (smoothed) (gm15sm-il)
GM15 (smoothed) - Gilbert Morris GM15 F1C class free flight flapper airfoil
| Details | Dat file | Parser | |
|
(gm15sm-il) GM15 (smoothed) Gilbert Morris GM15 F1C class free flight flapper airfoil Max thickness 6.7% at 20.5% chord. Max camber 4.8% at 49.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
GM15 (smoothed)
1.00000 0.00006
0.99754 0.00114
0.99070 0.00356
0.98037 0.00616
0.96698 0.00865
0.95044 0.01149
0.93064 0.01516
0.90775 0.01969
0.88202 0.02474
0.85370 0.03001
0.82309 0.03524
0.79048 0.04030
0.75616 0.04511
0.72043 0.04963
0.68359 0.05386
0.64594 0.05779
0.60778 0.06140
0.56937 0.06467
0.53099 0.06751
0.49265 0.06988
0.45435 0.07172
0.41638 0.07295
0.37887 0.07352
0.34204 0.07339
0.30609 0.07255
0.27120 0.07097
0.23760 0.06866
0.20549 0.06561
0.17504 0.06182
0.14648 0.05731
0.11999 0.05210
0.09576 0.04629
0.07395 0.04003
0.05468 0.03354
0.03811 0.02698
0.02433 0.02052
0.01338 0.01433
0.00548 0.00852
0.00098 0.00322
0.00000 -0.00019
0.00098 -0.00312
0.00548 -0.00634
0.01338 -0.00868
0.02433 -0.01036
0.03811 -0.01150
0.05468 -0.01210
0.07395 -0.01207
0.09576 -0.01136
0.11999 -0.00996
0.14648 -0.00785
0.17504 -0.00510
0.20549 -0.00179
0.23760 0.00191
0.27120 0.00586
0.30609 0.00988
0.34204 0.01379
0.37887 0.01741
0.41638 0.02060
0.45435 0.02324
0.49265 0.02526
0.53099 0.02661
0.56937 0.02732
0.60778 0.02740
0.64594 0.02692
0.68359 0.02594
0.72043 0.02456
0.75616 0.02287
0.79048 0.02088
0.82309 0.01858
0.85370 0.01598
0.88202 0.01317
0.90775 0.01033
0.93064 0.00765
0.95044 0.00528
0.96698 0.00332
0.98037 0.00179
0.99070 0.00075
0.99754 0.00017
1.00000 -0.00001
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GM15 (smoothed) (gm15sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| gm15sm-il | 50,000 | 9 | 45.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gm15sm-il | 50,000 | 5 | 46.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gm15sm-il | 100,000 | 9 | 66.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gm15sm-il | 100,000 | 5 | 66.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gm15sm-il | 200,000 | 9 | 91.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gm15sm-il | 200,000 | 5 | 86.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gm15sm-il | 500,000 | 9 | 123.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gm15sm-il | 500,000 | 5 | 112.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gm15sm-il | 1,000,000 | 9 | 146.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gm15sm-il | 1,000,000 | 5 | 119.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||