RAE(NPL) 5212 AIRFOIL (rae5212-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE(NPL) 5212 AIRFOIL (rae5212-il) Reynolds number: 500,000 Max Cl/Cd: 63.29 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5212-il-500000-n5.txt Download as CSV file: xf-rae5212-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8564 0.06619 0.06280 -0.0628 1.0000 0.0104
-14.500 -0.8812 0.05884 0.05526 -0.0673 1.0000 0.0104
-14.250 -0.8947 0.05397 0.05027 -0.0697 1.0000 0.0105
-14.000 -0.9123 0.04902 0.04514 -0.0717 1.0000 0.0105
-13.750 -0.9196 0.04576 0.04178 -0.0725 1.0000 0.0106
-13.500 -0.9255 0.04287 0.03879 -0.0729 1.0000 0.0107
-13.250 -0.9318 0.04015 0.03597 -0.0728 1.0000 0.0107
-13.000 -0.9371 0.03777 0.03347 -0.0722 1.0000 0.0108
-12.750 -0.9401 0.03582 0.03143 -0.0712 1.0000 0.0109
-12.500 -0.9423 0.03422 0.02976 -0.0697 1.0000 0.0110
-12.250 -0.9489 0.03259 0.02802 -0.0674 1.0000 0.0111
-12.000 -0.9599 0.03131 0.02664 -0.0637 1.0000 0.0112
-11.750 -0.9667 0.03033 0.02558 -0.0595 1.0000 0.0113
-11.500 -0.9662 0.02910 0.02422 -0.0565 1.0000 0.0114
-11.250 -0.9506 0.02769 0.02267 -0.0562 0.9988 0.0116
-11.000 -0.9265 0.02622 0.02103 -0.0575 0.9964 0.0119
-10.750 -0.9011 0.02486 0.01948 -0.0587 0.9943 0.0122
-10.500 -0.8775 0.02360 0.01806 -0.0593 0.9919 0.0125
-10.250 -0.8524 0.02248 0.01678 -0.0600 0.9892 0.0127
-10.000 -0.8255 0.02145 0.01561 -0.0609 0.9870 0.0130
-9.750 -0.7974 0.02049 0.01460 -0.0621 0.9851 0.0134
-9.500 -0.7673 0.01973 0.01379 -0.0635 0.9838 0.0137
-9.250 -0.7438 0.01907 0.01306 -0.0633 0.9798 0.0140
-9.000 -0.7160 0.01845 0.01239 -0.0639 0.9771 0.0145
-8.750 -0.6867 0.01778 0.01164 -0.0648 0.9749 0.0150
-8.500 -0.6559 0.01715 0.01092 -0.0660 0.9733 0.0156
-8.250 -0.6268 0.01649 0.01019 -0.0668 0.9711 0.0162
-8.000 -0.6040 0.01589 0.00958 -0.0663 0.9658 0.0167
-7.750 -0.5748 0.01536 0.00902 -0.0670 0.9630 0.0172
-7.500 -0.5438 0.01483 0.00846 -0.0681 0.9610 0.0179
-7.250 -0.5116 0.01430 0.00788 -0.0693 0.9593 0.0187
-7.000 -0.4893 0.01391 0.00743 -0.0684 0.9526 0.0194
-6.750 -0.4605 0.01338 0.00690 -0.0689 0.9489 0.0205
-6.500 -0.4295 0.01296 0.00647 -0.0699 0.9462 0.0216
-6.250 -0.4036 0.01259 0.00606 -0.0697 0.9406 0.0226
-6.000 -0.3757 0.01221 0.00564 -0.0698 0.9352 0.0237
-5.750 -0.3447 0.01177 0.00521 -0.0707 0.9315 0.0252
-5.500 -0.3177 0.01146 0.00488 -0.0707 0.9248 0.0268
-5.250 -0.2880 0.01114 0.00453 -0.0711 0.9192 0.0288
-5.000 -0.2573 0.01082 0.00421 -0.0719 0.9143 0.0316
-4.750 -0.2289 0.01055 0.00392 -0.0720 0.9073 0.0343
-4.500 -0.1982 0.01026 0.00363 -0.0727 0.9015 0.0390
-4.250 -0.1699 0.01000 0.00338 -0.0729 0.8943 0.0447
-4.000 -0.1407 0.00975 0.00314 -0.0732 0.8875 0.0530
-3.750 -0.1126 0.00952 0.00292 -0.0733 0.8803 0.0657
-3.500 -0.0852 0.00924 0.00271 -0.0733 0.8726 0.0880
-3.250 -0.0584 0.00888 0.00250 -0.0733 0.8655 0.1334
-3.000 -0.0333 0.00839 0.00226 -0.0730 0.8574 0.2098
-2.750 -0.0095 0.00765 0.00197 -0.0727 0.8502 0.3431
-2.500 0.0146 0.00714 0.00183 -0.0723 0.8424 0.4531
-2.000 0.0686 0.00694 0.00186 -0.0717 0.8285 0.5532
-1.750 0.0962 0.00695 0.00190 -0.0715 0.8218 0.5767
-1.500 0.1238 0.00698 0.00194 -0.0713 0.8151 0.5947
-1.250 0.1516 0.00702 0.00196 -0.0711 0.8080 0.6058
-1.000 0.1795 0.00705 0.00196 -0.0709 0.8003 0.6117
-0.750 0.2072 0.00707 0.00193 -0.0708 0.7903 0.6155
-0.500 0.2342 0.00711 0.00188 -0.0704 0.7756 0.6189
0.000 0.2860 0.00721 0.00182 -0.0691 0.7316 0.6250
0.250 0.3122 0.00729 0.00181 -0.0686 0.7115 0.6284
0.500 0.3376 0.00740 0.00180 -0.0679 0.6850 0.6318
0.750 0.3622 0.00755 0.00180 -0.0671 0.6515 0.6349
1.000 0.3869 0.00768 0.00183 -0.0663 0.6192 0.6377
1.250 0.4101 0.00789 0.00188 -0.0652 0.5748 0.6407
1.500 0.4314 0.00825 0.00197 -0.0639 0.5146 0.6439
1.750 0.4513 0.00874 0.00214 -0.0624 0.4387 0.6473
2.000 0.4717 0.00929 0.00233 -0.0610 0.3639 0.6505
2.250 0.4933 0.00974 0.00253 -0.0599 0.3024 0.6534
2.500 0.5159 0.01013 0.00272 -0.0590 0.2529 0.6566
2.750 0.5390 0.01049 0.00291 -0.0581 0.2113 0.6601
3.000 0.5623 0.01086 0.00311 -0.0573 0.1741 0.6637
3.250 0.5859 0.01121 0.00330 -0.0566 0.1433 0.6672
3.500 0.6099 0.01148 0.00350 -0.0559 0.1219 0.6703
3.750 0.6341 0.01175 0.00370 -0.0552 0.1060 0.6736
4.000 0.6585 0.01200 0.00391 -0.0546 0.0950 0.6770
4.250 0.6829 0.01225 0.00411 -0.0539 0.0874 0.6808
4.500 0.7079 0.01246 0.00432 -0.0534 0.0834 0.6844
4.750 0.7322 0.01269 0.00455 -0.0527 0.0794 0.6878
5.000 0.7561 0.01296 0.00481 -0.0520 0.0756 0.6914
5.250 0.7807 0.01316 0.00505 -0.0514 0.0740 0.6953
5.500 0.8050 0.01339 0.00530 -0.0508 0.0723 0.6992
5.750 0.8289 0.01362 0.00557 -0.0500 0.0706 0.7031
6.000 0.8523 0.01388 0.00586 -0.0493 0.0687 0.7079
6.250 0.8753 0.01418 0.00617 -0.0484 0.0668 0.7128
6.500 0.8973 0.01454 0.00655 -0.0474 0.0647 0.7177
6.750 0.9199 0.01482 0.00689 -0.0465 0.0637 0.7229
7.000 0.9427 0.01509 0.00721 -0.0456 0.0629 0.7287
7.250 0.9651 0.01537 0.00757 -0.0447 0.0619 0.7348
7.500 0.9870 0.01566 0.00793 -0.0437 0.0608 0.7419
7.750 1.0086 0.01596 0.00829 -0.0426 0.0597 0.7498
8.000 1.0296 0.01627 0.00868 -0.0415 0.0586 0.7593
8.250 1.0499 0.01659 0.00906 -0.0402 0.0573 0.7706
8.500 1.0683 0.01694 0.00948 -0.0386 0.0561 0.7859
8.750 1.0840 0.01736 0.01001 -0.0365 0.0548 0.8097
9.000 1.0984 0.01761 0.01051 -0.0340 0.0541 0.8734
9.250 1.1313 0.01796 0.01104 -0.0355 0.0533 1.0000
9.500 1.1502 0.01839 0.01151 -0.0341 0.0525 1.0000
9.750 1.1686 0.01884 0.01201 -0.0326 0.0517 1.0000
10.000 1.1873 0.01926 0.01248 -0.0313 0.0506 1.0000
10.250 1.2060 0.01967 0.01292 -0.0299 0.0495 1.0000
10.500 1.2244 0.02009 0.01337 -0.0286 0.0484 1.0000
10.750 1.2416 0.02058 0.01387 -0.0272 0.0472 1.0000
11.000 1.2565 0.02126 0.01457 -0.0254 0.0461 1.0000
11.250 1.2741 0.02174 0.01513 -0.0241 0.0453 1.0000
11.500 1.2915 0.02223 0.01569 -0.0228 0.0443 1.0000
11.750 1.3085 0.02275 0.01628 -0.0214 0.0432 1.0000
12.000 1.3247 0.02331 0.01690 -0.0200 0.0423 1.0000
12.250 1.3407 0.02388 0.01752 -0.0187 0.0412 1.0000
12.500 1.3559 0.02450 0.01816 -0.0173 0.0402 1.0000
12.750 1.3691 0.02528 0.01897 -0.0157 0.0393 1.0000
13.000 1.3824 0.02608 0.01986 -0.0143 0.0385 1.0000
13.250 1.3962 0.02687 0.02075 -0.0129 0.0377 1.0000
13.500 1.4093 0.02771 0.02168 -0.0115 0.0369 1.0000
13.750 1.4221 0.02858 0.02262 -0.0102 0.0359 1.0000
14.000 1.4346 0.02947 0.02356 -0.0090 0.0348 1.0000
14.250 1.4456 0.03049 0.02464 -0.0077 0.0339 1.0000
14.500 1.4555 0.03164 0.02584 -0.0064 0.0327 1.0000
14.750 1.4655 0.03282 0.02714 -0.0053 0.0319 1.0000
15.000 1.4749 0.03406 0.02848 -0.0041 0.0309 1.0000
15.250 1.4838 0.03538 0.02988 -0.0031 0.0298 1.0000
15.500 1.4911 0.03687 0.03144 -0.0021 0.0288 1.0000
15.750 1.4964 0.03860 0.03322 -0.0012 0.0278 1.0000
16.000 1.5026 0.04029 0.03506 -0.0004 0.0268 1.0000
16.250 1.5071 0.04220 0.03708 0.0002 0.0258 1.0000
16.500 1.5105 0.04429 0.03925 0.0007 0.0247 1.0000
16.750 1.5117 0.04666 0.04170 0.0011 0.0237 1.0000
17.000 1.5112 0.04933 0.04448 0.0012 0.0231 1.0000
17.250 1.5105 0.05216 0.04743 0.0012 0.0222 1.0000
17.500 1.5075 0.05537 0.05077 0.0008 0.0215 1.0000
17.750 1.5026 0.05899 0.05450 0.0000 0.0208 1.0000
18.000 1.4950 0.06317 0.05880 -0.0012 0.0203 1.0000
18.250 1.4839 0.06813 0.06388 -0.0030 0.0197 1.0000
18.500 1.4707 0.07367 0.06957 -0.0054 0.0194 1.0000
18.750 1.4557 0.07983 0.07590 -0.0084 0.0190 1.0000
19.000 1.4359 0.08717 0.08341 -0.0123 0.0188 1.0000
19.250 1.4100 0.09597 0.09240 -0.0173 0.0188 1.0000
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Polar data table (+)
Polar graphs
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