RAE(NPL) 5212 AIRFOIL (rae5212-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE(NPL) 5212 AIRFOIL (rae5212-il) Reynolds number: 100,000 Max Cl/Cd: 40.2 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5212-il-100000-n5.txt Download as CSV file: xf-rae5212-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE(NPL) 5212 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5135 0.09284 0.08728 -0.0459 1.0000 0.0325
-10.750 -0.5277 0.08495 0.07942 -0.0501 1.0000 0.0320
-10.500 -0.5536 0.07603 0.07049 -0.0556 1.0000 0.0315
-10.250 -0.5829 0.06915 0.06354 -0.0593 1.0000 0.0310
-10.000 -0.6128 0.06402 0.05833 -0.0607 1.0000 0.0306
-9.750 -0.6429 0.06045 0.05468 -0.0594 1.0000 0.0305
-9.500 -0.6689 0.05746 0.05157 -0.0565 1.0000 0.0303
-9.250 -0.6872 0.05422 0.04815 -0.0538 1.0000 0.0302
-9.000 -0.6995 0.05115 0.04485 -0.0511 1.0000 0.0303
-8.750 -0.7070 0.04813 0.04158 -0.0485 1.0000 0.0304
-8.500 -0.7101 0.04524 0.03840 -0.0460 1.0000 0.0306
-8.250 -0.7092 0.04256 0.03540 -0.0436 1.0000 0.0311
-8.000 -0.7052 0.04006 0.03254 -0.0413 1.0000 0.0320
-7.750 -0.6990 0.03748 0.02947 -0.0391 1.0000 0.0331
-7.500 -0.6887 0.03525 0.02688 -0.0372 1.0000 0.0339
-7.250 -0.6749 0.03364 0.02515 -0.0356 1.0000 0.0346
-7.000 -0.6558 0.03203 0.02336 -0.0350 0.9990 0.0354
-6.750 -0.6257 0.03030 0.02140 -0.0362 0.9954 0.0365
-6.500 -0.5958 0.02875 0.01959 -0.0372 0.9918 0.0383
-6.250 -0.5657 0.02737 0.01794 -0.0380 0.9880 0.0406
-6.000 -0.5349 0.02625 0.01682 -0.0393 0.9846 0.0427
-5.750 -0.5058 0.02517 0.01566 -0.0399 0.9805 0.0447
-5.500 -0.4755 0.02427 0.01459 -0.0406 0.9761 0.0478
-5.250 -0.4447 0.02330 0.01372 -0.0418 0.9727 0.0511
-5.000 -0.4183 0.02251 0.01290 -0.0419 0.9675 0.0545
-4.750 -0.3892 0.02174 0.01210 -0.0426 0.9628 0.0590
-4.500 -0.3569 0.02106 0.01142 -0.0439 0.9592 0.0656
-4.250 -0.3329 0.02039 0.01075 -0.0436 0.9527 0.0725
-4.000 -0.3029 0.01974 0.01013 -0.0445 0.9482 0.0850
-3.750 -0.2710 0.01904 0.00953 -0.0459 0.9446 0.1102
-3.500 -0.2492 0.01804 0.00896 -0.0456 0.9376 0.1853
-3.250 -0.2270 0.01649 0.00889 -0.0456 0.9330 0.4688
-3.000 -0.1990 0.01665 0.00920 -0.0452 0.9280 0.5610
-2.750 -0.1728 0.01687 0.00937 -0.0446 0.9215 0.6021
-2.500 -0.1425 0.01727 0.00979 -0.0442 0.9173 0.6398
-2.250 -0.1192 0.01768 0.01024 -0.0424 0.9112 0.6720
-2.000 -0.0925 0.01784 0.01038 -0.0416 0.9056 0.6905
-1.750 -0.0578 0.01776 0.01016 -0.0430 0.9021 0.6987
-1.500 -0.0296 0.01770 0.01003 -0.0431 0.8965 0.7036
-1.250 -0.0007 0.01763 0.00990 -0.0433 0.8908 0.7089
-1.000 0.0347 0.01752 0.00969 -0.0449 0.8871 0.7149
-0.750 0.0718 0.01740 0.00952 -0.0466 0.8845 0.7194
-0.500 0.0928 0.01742 0.00952 -0.0454 0.8758 0.7243
-0.250 0.1276 0.01732 0.00938 -0.0468 0.8717 0.7299
0.000 0.1651 0.01719 0.00923 -0.0486 0.8687 0.7345
0.250 0.1872 0.01723 0.00928 -0.0475 0.8600 0.7392
0.500 0.2225 0.01710 0.00915 -0.0489 0.8551 0.7444
0.750 0.2548 0.01700 0.00905 -0.0497 0.8485 0.7496
1.000 0.2846 0.01689 0.00898 -0.0498 0.8406 0.7542
1.250 0.3234 0.01665 0.00876 -0.0515 0.8355 0.7594
1.500 0.3500 0.01655 0.00869 -0.0511 0.8237 0.7652
1.750 0.3809 0.01630 0.00849 -0.0510 0.8117 0.7699
2.000 0.4146 0.01600 0.00823 -0.0515 0.7989 0.7754
2.250 0.4449 0.01566 0.00789 -0.0512 0.7785 0.7814
2.500 0.4760 0.01523 0.00745 -0.0506 0.7503 0.7865
2.750 0.5040 0.01498 0.00715 -0.0498 0.7175 0.7926
3.000 0.5305 0.01486 0.00699 -0.0489 0.6851 0.7989
3.250 0.5556 0.01481 0.00694 -0.0479 0.6503 0.8057
3.500 0.5808 0.01483 0.00685 -0.0469 0.5989 0.8133
3.750 0.6038 0.01502 0.00671 -0.0454 0.5199 0.8202
4.250 0.6359 0.01632 0.00712 -0.0408 0.3428 0.8394
4.500 0.6511 0.01709 0.00752 -0.0387 0.2697 0.8518
4.750 0.6685 0.01780 0.00796 -0.0371 0.2135 0.8672
5.000 0.6885 0.01846 0.00845 -0.0360 0.1754 0.8880
5.250 0.7155 0.01908 0.00900 -0.0362 0.1513 0.9223
5.500 0.7436 0.01972 0.00957 -0.0369 0.1378 1.0000
6.000 0.7865 0.02107 0.01080 -0.0354 0.1227 1.0000
6.250 0.8075 0.02177 0.01143 -0.0346 0.1169 1.0000
6.500 0.8287 0.02251 0.01213 -0.0338 0.1124 1.0000
6.750 0.8508 0.02321 0.01287 -0.0330 0.1084 1.0000
7.000 0.8728 0.02396 0.01360 -0.0323 0.1049 1.0000
7.250 0.8944 0.02482 0.01440 -0.0316 0.1017 1.0000
7.500 0.9176 0.02567 0.01528 -0.0311 0.0988 1.0000
7.750 0.9411 0.02648 0.01618 -0.0307 0.0958 1.0000
8.000 0.9649 0.02739 0.01713 -0.0303 0.0934 1.0000
8.250 0.9885 0.02833 0.01810 -0.0299 0.0911 1.0000
8.500 1.0122 0.02938 0.01912 -0.0296 0.0888 1.0000
8.750 1.0365 0.03054 0.02034 -0.0294 0.0866 1.0000
9.000 1.0592 0.03163 0.02162 -0.0289 0.0845 1.0000
9.250 1.0819 0.03284 0.02301 -0.0284 0.0826 1.0000
9.500 1.1039 0.03411 0.02443 -0.0278 0.0808 1.0000
9.750 1.1248 0.03537 0.02579 -0.0272 0.0791 1.0000
10.000 1.1453 0.03663 0.02711 -0.0266 0.0774 1.0000
10.250 1.1678 0.03829 0.02876 -0.0265 0.0756 1.0000
10.500 1.1817 0.03987 0.03067 -0.0248 0.0742 1.0000
10.750 1.1943 0.04169 0.03283 -0.0232 0.0729 1.0000
11.000 1.2044 0.04354 0.03498 -0.0213 0.0714 1.0000
11.250 1.2129 0.04536 0.03706 -0.0193 0.0699 1.0000
11.500 1.2195 0.04705 0.03897 -0.0172 0.0684 1.0000
11.750 1.2250 0.04868 0.04075 -0.0149 0.0671 1.0000
12.000 1.2304 0.05035 0.04255 -0.0128 0.0660 1.0000
12.250 1.2385 0.05211 0.04437 -0.0113 0.0649 1.0000
12.500 1.2368 0.05455 0.04699 -0.0090 0.0639 1.0000
12.750 1.2182 0.05740 0.05021 -0.0055 0.0632 1.0000
13.000 1.1971 0.06084 0.05400 -0.0028 0.0625 1.0000
13.250 1.1736 0.06487 0.05834 -0.0012 0.0618 1.0000
13.500 1.1467 0.06975 0.06351 -0.0007 0.0614 1.0000
13.750 1.1138 0.07591 0.06995 -0.0017 0.0612 1.0000
14.000 1.0709 0.08444 0.07874 -0.0053 0.0613 1.0000
14.250 1.0041 0.09933 0.09389 -0.0146 0.0622 1.0000
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Polar data table (+)
Polar graphs
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