DAE-31 AIRFOIL (dae31-il)
DAE-31 AIRFOIL - Drela DAE31 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(dae31-il) DAE-31 AIRFOIL Drela DAE31 low Reynolds number airfoil Max thickness 11.1% at 29.3% chord. Max camber 6.7% at 47% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
DAE-31 AIRFOIL
42.0 41.0
0.0000000 0.0000000
0.0003482 0.0040557
0.0025714 0.0102478
0.0072528 0.0181120
0.0151525 0.0274887
0.0266957 0.0379531
0.0416829 0.0487251
0.0597202 0.0592106
0.0803468 0.0690522
0.1030908 0.0780938
0.1275122 0.0862261
0.1532431 0.0934191
0.1799774 0.0996865
0.2074701 0.1050483
0.2355553 0.1095233
0.2641038 0.1131615
0.2929977 0.1159949
0.3221600 0.1180434
0.3515427 0.1193380
0.3810937 0.1199127
0.4107560 0.1197894
0.4404975 0.1189772
0.4702895 0.1175029
0.5000657 0.1153907
0.5297562 0.1126354
0.5593120 0.1092310
0.5887031 0.1051596
0.6179285 0.1004011
0.6470113 0.0949415
0.6760014 0.0887678
0.7049618 0.0818952
0.7340045 0.0743106
0.7633666 0.0660061
0.7933150 0.0570929
0.8239395 0.0477859
0.8543990 0.0386040
0.8847364 0.0297089
0.9151255 0.0211589
0.9422911 0.0139124
0.9648269 0.0082008
0.9836681 0.0036705
1.0000000 0.0000000
0.0000000 0.0000000
0.0001807 -.0032476
0.0011704 -.0071260
0.0029628 -.0100572
0.0056908 -.0123330
0.0099867 -.0140530
0.0172463 -.0152927
0.0297287 -.0159839
0.0490207 -.0156330
0.0742842 -.0141843
0.1029554 -.0119380
0.1333124 -.0092209
0.1645073 -.0062945
0.1961702 -.0032978
0.2281120 -.0003260
0.2601610 0.0025598
0.2921169 0.0053196
0.3239840 0.0079314
0.3557761 0.0103711
0.3874933 0.0126278
0.4191336 0.0146695
0.4507050 0.0164751
0.4822036 0.0180277
0.5136282 0.0192952
0.5450060 0.0202477
0.5763610 0.0208932
0.6076820 0.0212357
0.6389643 0.0212622
0.6702207 0.0209726
0.7014622 0.0203751
0.7326788 0.0194885
0.7638477 0.0183119
0.7949666 0.0168263
0.8260636 0.0150337
0.8572249 0.0129321
0.8888093 0.0105107
0.9192797 0.0079207
0.9456010 0.0055029
0.9670691 0.0034138
0.9848812 0.0015830
1.0000000 0.0000000
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Polars for DAE-31 AIRFOIL (dae31-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| dae31-il | 50,000 | 9 | 10 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae31-il | 50,000 | 5 | 25.9 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae31-il | 100,000 | 9 | 56.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae31-il | 100,000 | 5 | 57.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae31-il | 200,000 | 9 | 91.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae31-il | 200,000 | 5 | 90.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae31-il | 500,000 | 9 | 139.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae31-il | 500,000 | 5 | 128.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae31-il | 1,000,000 | 9 | 173.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae31-il | 1,000,000 | 5 | 151.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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