RAE(NPL) 5212 AIRFOIL (rae5212-il)
RAE(NPL) 5212 AIRFOIL - RAE(NPL) 5212 transonic airfoil
| Details | Dat file | Parser | |
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(rae5212-il) RAE(NPL) 5212 AIRFOIL RAE(NPL) 5212 transonic airfoil Max thickness 11.9% at 35.5% chord. Max camber 1.8% at 69.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAE(NPL) 5212 AIRFOIL
42. 42.
0.00000 0.00000
0.00050 0.00424
0.00100 0.00603
0.00160 0.00765
0.00241 0.00943
0.00350 0.01142
0.00500 0.01371
0.00650 0.01567
0.00800 0.01743
0.00961 0.01914
0.01500 0.02407
0.02153 0.02877
0.03000 0.03341
0.03806 0.03689
0.05904 0.04325
0.08427 0.04904
0.11349 0.05427
0.14645 0.05900
0.18280 0.06309
0.22221 0.06647
0.26430 0.06918
0.30866 0.07114
0.35486 0.07231
0.40245 0.07261
0.45099 0.07207
0.50000 0.07051
0.54901 0.06791
0.59755 0.06424
0.64514 0.05948
0.69134 0.05402
0.73570 0.04815
0.77779 0.04202
0.81720 0.03579
0.85355 0.02976
0.88651 0.02403
0.91573 0.01863
0.94096 0.01336
0.96194 0.00861
0.97847 0.00465
0.99039 0.00197
0.99759 0.00047
1.00000 0.00000
0.00000 0.00000
0.00050 -0.00347
0.00100 -0.00482
0.00160 -0.00599
0.00241 -0.00723
0.00350 -0.00855
0.00500 -0.01001
0.00650 -0.01121
0.00800 -0.01224
0.00961 -0.01322
0.01500 -0.01586
0.02153 -0.01831
0.03000 -0.02090
0.03806 -0.02295
0.05904 -0.02723
0.08427 -0.03132
0.11349 -0.03509
0.14645 -0.03840
0.18280 -0.04141
0.22221 -0.04385
0.26430 -0.04580
0.30866 -0.04696
0.35486 -0.04715
0.40245 -0.04619
0.45099 -0.04401
0.50000 -0.04051
0.54901 -0.03539
0.59755 -0.02954
0.64514 -0.02324
0.69134 -0.01736
0.73570 -0.01245
0.77779 -0.00844
0.81720 -0.00537
0.85355 -0.00310
0.88651 -0.00153
0.91573 -0.00055
0.94096 -0.00006
0.96194 0.00011
0.97847 0.00009
0.99039 0.00005
0.99759 0.00001
1.00000 0.00000
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Polars for RAE(NPL) 5212 AIRFOIL (rae5212-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rae5212-il | 50,000 | 9 | 31.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5212-il | 50,000 | 5 | 30.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5212-il | 100,000 | 9 | 47.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5212-il | 100,000 | 5 | 40.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5212-il | 200,000 | 9 | 57.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5212-il | 200,000 | 5 | 48.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5212-il | 500,000 | 9 | 69.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5212-il | 500,000 | 5 | 63.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae5212-il | 1,000,000 | 9 | 76.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae5212-il | 1,000,000 | 5 | 80.3 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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