davissm (davissm-il)
davissm - Davis 3R F1B free flight airfoil (smoothed)
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(davissm-il) davissm Davis 3R F1B free flight airfoil (smoothed) Max thickness 5.9% at 30.6% chord. Max camber 5.9% at 45.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
davissm
1.00000 0.00588
0.99754 0.00719
0.99070 0.01009
0.98037 0.01307
0.96698 0.01585
0.95044 0.01919
0.93064 0.02337
0.90775 0.02831
0.88202 0.03384
0.85370 0.03980
0.82309 0.04598
0.79048 0.05217
0.75616 0.05819
0.72043 0.06387
0.68359 0.06908
0.64594 0.07373
0.60778 0.07774
0.56937 0.08107
0.53099 0.08369
0.49265 0.08559
0.45435 0.08675
0.41638 0.08712
0.37887 0.08671
0.34204 0.08547
0.30609 0.08342
0.27120 0.08053
0.23760 0.07682
0.20549 0.07230
0.17504 0.06696
0.14648 0.06085
0.11999 0.05408
0.09576 0.04697
0.07395 0.04001
0.05468 0.03359
0.03811 0.02757
0.02433 0.02159
0.01338 0.01552
0.00548 0.00957
0.00098 0.00384
0.00000 -0.00003
0.00098 -0.00354
0.00548 -0.00727
0.01338 -0.00901
0.02433 -0.00845
0.03811 -0.00648
0.05468 -0.00385
0.07395 -0.00091
0.09576 0.00220
0.11999 0.00545
0.14648 0.00879
0.17504 0.01218
0.20549 0.01557
0.23760 0.01884
0.27120 0.02191
0.30609 0.02468
0.34204 0.02707
0.37887 0.02901
0.41638 0.03047
0.45435 0.03140
0.49265 0.03181
0.53099 0.03168
0.56937 0.03104
0.60778 0.02987
0.64594 0.02822
0.68359 0.02613
0.72043 0.02364
0.75616 0.02082
0.79048 0.01776
0.82309 0.01453
0.85370 0.01124
0.88202 0.00798
0.90775 0.00486
0.93064 0.00191
0.95044 -0.00086
0.96698 -0.00339
0.98037 -0.00530
0.99070 -0.00620
0.99754 -0.00612
1.00000 -0.00590
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Polars for davissm (davissm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| davissm-il | 50,000 | 9 | 45.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 50,000 | 5 | 45.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davissm-il | 100,000 | 9 | 70.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 100,000 | 5 | 69.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davissm-il | 200,000 | 9 | 96.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 200,000 | 5 | 92.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davissm-il | 500,000 | 9 | 131.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 500,000 | 5 | 118.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davissm-il | 1,000,000 | 9 | 154.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 1,000,000 | 5 | 128.8 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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