RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il) Reynolds number: 200,000 Max Cl/Cd: 48.68 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5213-il-200000-n5.txt Download as CSV file: xf-rae5213-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE(NPL) 5213 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5591 0.08960 0.08556 -0.0257 1.0000 0.0168
-10.250 -0.5667 0.08329 0.07928 -0.0293 1.0000 0.0167
-10.000 -0.5786 0.07528 0.07131 -0.0345 1.0000 0.0165
-9.750 -0.6096 0.06329 0.05924 -0.0441 1.0000 0.0163
-9.500 -0.6378 0.05658 0.05241 -0.0485 1.0000 0.0161
-9.250 -0.6618 0.05168 0.04733 -0.0497 1.0000 0.0161
-9.000 -0.6814 0.04573 0.04103 -0.0498 1.0000 0.0161
-8.750 -0.6921 0.04015 0.03498 -0.0491 1.0000 0.0163
-8.500 -0.6959 0.03482 0.02902 -0.0478 1.0000 0.0167
-8.250 -0.6858 0.03222 0.02607 -0.0466 1.0000 0.0172
-8.000 -0.6686 0.03136 0.02519 -0.0457 1.0000 0.0177
-7.750 -0.6529 0.02988 0.02353 -0.0446 1.0000 0.0185
-7.500 -0.6383 0.02750 0.02075 -0.0433 1.0000 0.0193
-7.250 -0.6223 0.02508 0.01780 -0.0418 1.0000 0.0200
-7.000 -0.6038 0.02386 0.01651 -0.0407 1.0000 0.0205
-6.750 -0.5847 0.02282 0.01539 -0.0395 1.0000 0.0210
-6.500 -0.5653 0.02186 0.01431 -0.0383 1.0000 0.0219
-6.250 -0.5455 0.02080 0.01299 -0.0370 1.0000 0.0233
-6.000 -0.5141 0.01983 0.01202 -0.0382 0.9969 0.0244
-5.750 -0.4811 0.01887 0.01098 -0.0396 0.9932 0.0255
-5.500 -0.4487 0.01790 0.00988 -0.0407 0.9891 0.0268
-5.250 -0.4148 0.01714 0.00916 -0.0423 0.9855 0.0285
-5.000 -0.3826 0.01650 0.00846 -0.0434 0.9807 0.0305
-4.750 -0.3493 0.01576 0.00773 -0.0448 0.9764 0.0319
-4.500 -0.3160 0.01519 0.00717 -0.0462 0.9719 0.0340
-4.250 -0.2837 0.01464 0.00660 -0.0473 0.9662 0.0365
-4.000 -0.2484 0.01412 0.00609 -0.0490 0.9625 0.0391
-3.750 -0.2175 0.01366 0.00563 -0.0497 0.9556 0.0423
-3.500 -0.1833 0.01324 0.00519 -0.0511 0.9507 0.0467
-3.250 -0.1514 0.01281 0.00478 -0.0520 0.9443 0.0530
-3.000 -0.1190 0.01235 0.00439 -0.0530 0.9379 0.0675
-2.750 -0.0863 0.01173 0.00403 -0.0542 0.9321 0.1219
-2.500 -0.0586 0.01068 0.00365 -0.0550 0.9234 0.2856
-2.250 -0.0295 0.00980 0.00361 -0.0556 0.9168 0.4947
-2.000 -0.0016 0.00973 0.00376 -0.0553 0.9074 0.5717
-1.750 0.0291 0.00982 0.00395 -0.0552 0.9001 0.6240
-1.500 0.0569 0.00995 0.00410 -0.0546 0.8896 0.6550
-1.250 0.0863 0.00996 0.00411 -0.0544 0.8805 0.6681
-1.000 0.1157 0.00994 0.00401 -0.0544 0.8701 0.6752
-0.750 0.1442 0.00989 0.00395 -0.0542 0.8592 0.6797
-0.500 0.1729 0.00985 0.00385 -0.0539 0.8459 0.6850
-0.250 0.2011 0.00983 0.00375 -0.0535 0.8304 0.6906
0.000 0.2283 0.00980 0.00368 -0.0530 0.8133 0.6951
0.250 0.2553 0.00979 0.00360 -0.0523 0.7925 0.6998
0.500 0.2815 0.00980 0.00350 -0.0514 0.7618 0.7050
0.750 0.3077 0.00987 0.00340 -0.0506 0.7279 0.7103
1.000 0.3336 0.00992 0.00337 -0.0498 0.6975 0.7144
1.250 0.3599 0.01001 0.00336 -0.0491 0.6684 0.7193
1.500 0.3861 0.01013 0.00336 -0.0485 0.6327 0.7246
1.750 0.4112 0.01030 0.00337 -0.0476 0.5834 0.7292
2.000 0.4343 0.01063 0.00340 -0.0464 0.5097 0.7339
2.250 0.4554 0.01124 0.00354 -0.0451 0.4080 0.7393
2.750 0.4979 0.01275 0.00410 -0.0432 0.2038 0.7495
3.000 0.5218 0.01326 0.00439 -0.0426 0.1599 0.7554
3.250 0.5472 0.01364 0.00467 -0.0422 0.1396 0.7619
3.500 0.5723 0.01395 0.00495 -0.0416 0.1271 0.7675
3.750 0.5974 0.01427 0.00525 -0.0411 0.1179 0.7741
4.000 0.6228 0.01456 0.00557 -0.0406 0.1112 0.7813
4.250 0.6474 0.01489 0.00590 -0.0400 0.1053 0.7894
4.500 0.6721 0.01523 0.00626 -0.0394 0.1001 0.7982
4.750 0.6965 0.01552 0.00661 -0.0387 0.0950 0.8079
5.000 0.7202 0.01596 0.00704 -0.0380 0.0901 0.8193
5.250 0.7450 0.01620 0.00739 -0.0373 0.0852 0.8342
5.500 0.7684 0.01650 0.00774 -0.0365 0.0806 0.8557
5.750 0.7922 0.01675 0.00813 -0.0356 0.0764 0.8976
6.000 0.8222 0.01707 0.00851 -0.0362 0.0719 1.0000
6.250 0.8474 0.01755 0.00897 -0.0359 0.0681 1.0000
6.500 0.8728 0.01797 0.00942 -0.0356 0.0641 1.0000
6.750 0.8973 0.01846 0.00988 -0.0352 0.0609 1.0000
7.000 0.9220 0.01894 0.01041 -0.0348 0.0573 1.0000
7.250 0.9459 0.01948 0.01092 -0.0343 0.0546 1.0000
7.500 0.9697 0.02008 0.01159 -0.0337 0.0516 1.0000
7.750 0.9931 0.02064 0.01216 -0.0332 0.0491 1.0000
8.000 1.0158 0.02132 0.01287 -0.0325 0.0468 1.0000
8.250 1.0385 0.02199 0.01361 -0.0319 0.0446 1.0000
8.500 1.0605 0.02268 0.01430 -0.0312 0.0429 1.0000
8.750 1.0819 0.02353 0.01522 -0.0304 0.0415 1.0000
9.000 1.1031 0.02441 0.01620 -0.0295 0.0400 1.0000
9.250 1.1239 0.02527 0.01713 -0.0287 0.0388 1.0000
9.500 1.1440 0.02612 0.01802 -0.0278 0.0379 1.0000
9.750 1.1631 0.02712 0.01908 -0.0269 0.0369 1.0000
10.000 1.1823 0.02822 0.02035 -0.0259 0.0359 1.0000
10.250 1.2005 0.02929 0.02156 -0.0248 0.0349 1.0000
10.500 1.2178 0.03035 0.02272 -0.0237 0.0341 1.0000
10.750 1.2342 0.03142 0.02386 -0.0225 0.0335 1.0000
11.000 1.2494 0.03257 0.02509 -0.0213 0.0330 1.0000
11.250 1.2629 0.03394 0.02655 -0.0199 0.0326 1.0000
11.500 1.2736 0.03558 0.02843 -0.0182 0.0321 1.0000
11.750 1.2808 0.03730 0.03038 -0.0161 0.0317 1.0000
12.000 1.2853 0.03911 0.03242 -0.0139 0.0313 1.0000
12.250 1.2877 0.04106 0.03457 -0.0118 0.0309 1.0000
12.500 1.2879 0.04313 0.03684 -0.0098 0.0306 1.0000
12.750 1.2864 0.04538 0.03928 -0.0082 0.0303 1.0000
13.000 1.2833 0.04783 0.04191 -0.0069 0.0300 1.0000
13.250 1.2785 0.05059 0.04486 -0.0061 0.0298 1.0000
13.500 1.2725 0.05362 0.04805 -0.0058 0.0295 1.0000
13.750 1.2641 0.05718 0.05178 -0.0061 0.0294 1.0000
14.000 1.2543 0.06117 0.05594 -0.0071 0.0292 1.0000
14.250 1.2385 0.06639 0.06136 -0.0091 0.0291 1.0000
14.500 1.2199 0.07251 0.06769 -0.0123 0.0290 1.0000
14.750 1.1702 0.08542 0.08099 -0.0210 0.0291 1.0000
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