DAE-51 AIRFOIL (dae51-il)
DAE-51 AIRFOIL - Drela DAE51 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(dae51-il) DAE-51 AIRFOIL Drela DAE51 low Reynolds number airfoil Max thickness 9.4% at 30.7% chord. Max camber 4% at 46.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
DAE-51 AIRFOIL
40.0 41.0
0.0000000 0.0000000
0.0041977 0.0095700
0.0100356 0.0154241
0.0200350 0.0227665
0.0348482 0.0311300
0.0540182 0.0397400
0.0764527 0.0479203
0.1011350 0.0553181
0.1273392 0.0618114
0.1546283 0.0674128
0.1826904 0.0721660
0.2113082 0.0761239
0.2403358 0.0793401
0.2696742 0.0818597
0.2992332 0.0837195
0.3289599 0.0849515
0.3588182 0.0855796
0.3887731 0.0856308
0.4187877 0.0851351
0.4488457 0.0841175
0.4789282 0.0826078
0.5089862 0.0806341
0.5389917 0.0782224
0.5689247 0.0753936
0.5987790 0.0721627
0.6285808 0.0685028
0.6583750 0.0644109
0.6882508 0.0599010
0.7182678 0.0550003
0.7484503 0.0497218
0.7787921 0.0441214
0.8092952 0.0382822
0.8399634 0.0322472
0.8707898 0.0260833
0.9016322 0.0199055
0.9315834 0.0139837
0.9574376 0.0089976
0.9758121 0.0055268
0.9891618 0.0030357
0.9999979 0.0010000
0.0000000 0.0000000
0.0001209 -.0014656
0.0010059 -.0040753
0.0027994 -.0064104
0.0060276 -.0085090
0.0119707 -.0105878
0.0227109 -.0126946
0.0403478 -.0145033
0.0642490 -.0156413
0.0918984 -.0160685
0.1213212 -.0159319
0.1515756 -.0154033
0.1822458 -.0145914
0.2131627 -.0135661
0.2442524 -.0123857
0.2754751 -.0110962
0.3068076 -.0097325
0.3382381 -.0083288
0.3697316 -.0069239
0.4011892 -.0055351
0.4326007 -.0041804
0.4639783 -.0028737
0.4953260 -.0016220
0.5266438 -.0004364
0.5579286 0.0006722
0.5891795 0.0016938
0.6203865 0.0026153
0.6515426 0.0034188
0.6826429 0.0040872
0.7136883 0.0045996
0.7446840 0.0049369
0.7756378 0.0050861
0.8065398 0.0050393
0.8373671 0.0047795
0.8681286 0.0042725
0.8989804 0.0034777
0.9298645 0.0023879
0.9565697 0.0012247
0.9753916 0.0002834
0.9889824 -.0004325
1.0000000 -.0010000
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Polars for DAE-51 AIRFOIL (dae51-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| dae51-il | 50,000 | 9 | 39.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 50,000 | 5 | 41 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 100,000 | 9 | 62.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 100,000 | 5 | 63.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 200,000 | 9 | 87.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 200,000 | 5 | 84.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 500,000 | 9 | 121.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 500,000 | 5 | 110.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 1,000,000 | 9 | 144.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 1,000,000 | 5 | 127.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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