RAE 5214 AIRFOIL (rae5214-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: RAE 5214 AIRFOIL (rae5214-il) Reynolds number: 100,000 Max Cl/Cd: 35.69 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5214-il-100000-n5.txt Download as CSV file: xf-rae5214-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE 5214 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5464 0.08519 0.07965 -0.0306 1.0000 0.0309
-9.500 -0.5524 0.07899 0.07348 -0.0346 1.0000 0.0304
-9.250 -0.5675 0.07173 0.06622 -0.0400 1.0000 0.0300
-9.000 -0.5879 0.06586 0.06031 -0.0440 1.0000 0.0296
-8.750 -0.6079 0.06105 0.05539 -0.0459 1.0000 0.0292
-8.500 -0.6210 0.05626 0.05040 -0.0469 1.0000 0.0289
-8.250 -0.6278 0.05181 0.04568 -0.0469 1.0000 0.0288
-8.000 -0.6293 0.04769 0.04124 -0.0465 1.0000 0.0287
-7.750 -0.6259 0.04394 0.03715 -0.0456 1.0000 0.0288
-7.500 -0.6181 0.04069 0.03354 -0.0447 1.0000 0.0293
-7.250 -0.6082 0.03749 0.02987 -0.0436 1.0000 0.0305
-7.000 -0.5957 0.03442 0.02624 -0.0423 1.0000 0.0315
-6.750 -0.5785 0.03289 0.02465 -0.0413 1.0000 0.0323
-6.500 -0.5612 0.03092 0.02242 -0.0402 1.0000 0.0329
-6.250 -0.5428 0.02901 0.02024 -0.0389 1.0000 0.0337
-6.000 -0.5235 0.02723 0.01814 -0.0377 1.0000 0.0349
-5.750 -0.5037 0.02583 0.01653 -0.0365 1.0000 0.0366
-5.500 -0.4838 0.02482 0.01549 -0.0354 1.0000 0.0384
-5.250 -0.4631 0.02360 0.01411 -0.0341 1.0000 0.0399
-5.000 -0.4423 0.02248 0.01284 -0.0328 1.0000 0.0414
-4.750 -0.4221 0.02168 0.01210 -0.0318 1.0000 0.0436
-4.500 -0.4013 0.02089 0.01123 -0.0306 1.0000 0.0462
-4.250 -0.3808 0.02005 0.01041 -0.0294 1.0000 0.0480
-4.000 -0.3601 0.01940 0.00981 -0.0285 1.0000 0.0511
-3.750 -0.3361 0.01877 0.00914 -0.0280 0.9990 0.0547
-3.500 -0.3025 0.01811 0.00851 -0.0296 0.9946 0.0590
-3.250 -0.2694 0.01750 0.00791 -0.0309 0.9897 0.0659
-3.000 -0.2348 0.01694 0.00737 -0.0326 0.9854 0.0780
-2.750 -0.2022 0.01624 0.00686 -0.0340 0.9801 0.1095
-2.500 -0.1717 0.01443 0.00636 -0.0362 0.9760 0.3684
-2.250 -0.1439 0.01417 0.00689 -0.0359 0.9700 0.5698
-2.000 -0.1132 0.01453 0.00739 -0.0357 0.9639 0.6437
-1.750 -0.0861 0.01490 0.00782 -0.0346 0.9570 0.6920
-1.500 -0.0564 0.01508 0.00805 -0.0341 0.9512 0.7174
-1.250 -0.0234 0.01507 0.00795 -0.0352 0.9452 0.7280
-1.000 0.0089 0.01503 0.00787 -0.0359 0.9388 0.7343
-0.750 0.0471 0.01500 0.00778 -0.0379 0.9344 0.7418
-0.500 0.0769 0.01496 0.00771 -0.0383 0.9259 0.7482
-0.250 0.1147 0.01489 0.00762 -0.0400 0.9199 0.7546
0.000 0.1480 0.01481 0.00752 -0.0409 0.9099 0.7619
0.250 0.1874 0.01458 0.00731 -0.0425 0.8991 0.7674
0.500 0.2257 0.01429 0.00703 -0.0436 0.8841 0.7737
0.750 0.2581 0.01402 0.00674 -0.0436 0.8627 0.7803
1.000 0.2883 0.01371 0.00643 -0.0428 0.8351 0.7862
1.250 0.3179 0.01347 0.00615 -0.0421 0.8039 0.7930
1.500 0.3471 0.01332 0.00597 -0.0415 0.7759 0.7995
1.750 0.3736 0.01323 0.00587 -0.0405 0.7437 0.8066
2.000 0.4010 0.01318 0.00575 -0.0397 0.7016 0.8142
2.250 0.4264 0.01320 0.00561 -0.0384 0.6352 0.8216
2.750 0.4659 0.01448 0.00558 -0.0343 0.3611 0.8395
3.000 0.4853 0.01536 0.00590 -0.0330 0.2583 0.8501
3.250 0.5074 0.01594 0.00624 -0.0320 0.2143 0.8628
3.500 0.5306 0.01640 0.00659 -0.0311 0.1901 0.8785
3.750 0.5555 0.01682 0.00697 -0.0306 0.1726 0.8997
4.250 0.6159 0.01777 0.00787 -0.0320 0.1465 1.0000
4.500 0.6421 0.01837 0.00839 -0.0320 0.1374 1.0000
4.750 0.6680 0.01896 0.00890 -0.0319 0.1293 1.0000
5.000 0.6939 0.01958 0.00951 -0.0318 0.1220 1.0000
5.250 0.7195 0.02021 0.01008 -0.0316 0.1154 1.0000
5.500 0.7450 0.02091 0.01077 -0.0313 0.1092 1.0000
5.750 0.7702 0.02158 0.01142 -0.0311 0.1031 1.0000
6.000 0.7952 0.02234 0.01218 -0.0308 0.0974 1.0000
6.250 0.8202 0.02303 0.01288 -0.0305 0.0916 1.0000
6.500 0.8446 0.02385 0.01370 -0.0301 0.0865 1.0000
6.750 0.8692 0.02462 0.01455 -0.0297 0.0813 1.0000
7.000 0.8930 0.02549 0.01537 -0.0293 0.0773 1.0000
7.250 0.9171 0.02640 0.01647 -0.0288 0.0727 1.0000
7.500 0.9402 0.02722 0.01724 -0.0284 0.0695 1.0000
7.750 0.9636 0.02843 0.01866 -0.0278 0.0657 1.0000
8.000 0.9861 0.02936 0.01966 -0.0272 0.0627 1.0000
8.250 1.0080 0.03046 0.02083 -0.0266 0.0602 1.0000
8.500 1.0292 0.03198 0.02261 -0.0259 0.0575 1.0000
8.750 1.0500 0.03327 0.02401 -0.0252 0.0557 1.0000
9.000 1.0705 0.03437 0.02512 -0.0245 0.0542 1.0000
9.250 1.0872 0.03655 0.02771 -0.0234 0.0522 1.0000
9.500 1.1032 0.03843 0.02986 -0.0223 0.0504 1.0000
9.750 1.1194 0.03990 0.03148 -0.0213 0.0491 1.0000
10.000 1.1355 0.04138 0.03303 -0.0204 0.0482 1.0000
10.250 1.1452 0.04393 0.03589 -0.0189 0.0474 1.0000
10.500 1.1450 0.04758 0.04005 -0.0169 0.0466 1.0000
10.750 1.1393 0.05137 0.04428 -0.0147 0.0459 1.0000
11.000 1.1262 0.05521 0.04849 -0.0122 0.0455 1.0000
11.250 1.1053 0.05923 0.05282 -0.0097 0.0452 1.0000
11.500 1.0767 0.06430 0.05818 -0.0088 0.0451 1.0000
11.750 1.0367 0.07166 0.06583 -0.0109 0.0453 1.0000
12.000 0.9592 0.08891 0.08341 -0.0231 0.0462 1.0000
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Polar data table (+)
Polar graphs
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