RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il) Reynolds number: 500,000 Max Cl/Cd: 68.27 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5213-il-500000-n5.txt Download as CSV file: xf-rae5213-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.8598 0.04849 0.04525 -0.0534 1.0000 0.0088
-12.000 -0.8975 0.04100 0.03743 -0.0573 1.0000 0.0089
-11.750 -0.9238 0.03635 0.03249 -0.0577 1.0000 0.0089
-11.500 -0.9375 0.03290 0.02872 -0.0563 1.0000 0.0090
-11.250 -0.9387 0.02988 0.02536 -0.0551 1.0000 0.0092
-11.000 -0.9310 0.02773 0.02295 -0.0539 1.0000 0.0092
-10.750 -0.9192 0.02607 0.02111 -0.0529 1.0000 0.0094
-10.500 -0.9034 0.02494 0.01987 -0.0519 1.0000 0.0096
-10.250 -0.8861 0.02397 0.01881 -0.0509 1.0000 0.0097
-10.000 -0.8679 0.02308 0.01783 -0.0500 1.0000 0.0098
-9.750 -0.8489 0.02230 0.01697 -0.0491 1.0000 0.0101
-9.500 -0.8299 0.02146 0.01603 -0.0481 1.0000 0.0103
-9.250 -0.8109 0.02057 0.01503 -0.0470 1.0000 0.0105
-9.000 -0.7919 0.01966 0.01399 -0.0459 1.0000 0.0109
-8.750 -0.7728 0.01875 0.01294 -0.0447 1.0000 0.0112
-8.500 -0.7536 0.01787 0.01192 -0.0435 1.0000 0.0116
-8.250 -0.7308 0.01727 0.01128 -0.0430 0.9995 0.0118
-8.000 -0.6989 0.01675 0.01073 -0.0442 0.9972 0.0122
-7.750 -0.6667 0.01624 0.01017 -0.0455 0.9947 0.0127
-7.500 -0.6359 0.01561 0.00947 -0.0464 0.9918 0.0133
-7.250 -0.6044 0.01498 0.00873 -0.0475 0.9889 0.0140
-7.000 -0.5720 0.01442 0.00814 -0.0487 0.9864 0.0145
-6.750 -0.5393 0.01402 0.00773 -0.0500 0.9840 0.0152
-6.500 -0.5085 0.01361 0.00728 -0.0507 0.9800 0.0160
-6.250 -0.4758 0.01320 0.00680 -0.0519 0.9769 0.0171
-6.000 -0.4425 0.01281 0.00643 -0.0532 0.9742 0.0181
-5.750 -0.4137 0.01246 0.00605 -0.0535 0.9677 0.0192
-5.500 -0.3818 0.01204 0.00559 -0.0544 0.9630 0.0203
-5.250 -0.3523 0.01160 0.00516 -0.0549 0.9566 0.0212
-5.000 -0.3208 0.01123 0.00478 -0.0557 0.9511 0.0222
-4.750 -0.2904 0.01093 0.00443 -0.0562 0.9444 0.0234
-4.500 -0.2603 0.01054 0.00405 -0.0567 0.9371 0.0247
-4.250 -0.2310 0.01025 0.00374 -0.0570 0.9291 0.0259
-4.000 -0.2019 0.00999 0.00346 -0.0571 0.9200 0.0271
-3.750 -0.1738 0.00972 0.00318 -0.0571 0.9105 0.0289
-3.250 -0.1177 0.00930 0.00273 -0.0569 0.8908 0.0338
-3.000 -0.0899 0.00911 0.00253 -0.0567 0.8812 0.0386
-2.750 -0.0624 0.00891 0.00236 -0.0565 0.8701 0.0490
-2.500 -0.0351 0.00869 0.00219 -0.0563 0.8585 0.0686
-2.250 -0.0081 0.00839 0.00201 -0.0561 0.8463 0.1132
-2.000 0.0184 0.00792 0.00182 -0.0560 0.8336 0.2009
-1.750 0.0439 0.00721 0.00159 -0.0559 0.8185 0.3551
-1.500 0.0695 0.00674 0.00150 -0.0556 0.8007 0.4828
-1.250 0.0961 0.00661 0.00155 -0.0551 0.7860 0.5554
-1.000 0.1234 0.00662 0.00161 -0.0547 0.7732 0.5933
-0.750 0.1505 0.00670 0.00165 -0.0542 0.7556 0.6170
-0.500 0.1773 0.00679 0.00167 -0.0537 0.7296 0.6293
-0.250 0.2038 0.00692 0.00164 -0.0531 0.6968 0.6351
0.000 0.2306 0.00706 0.00162 -0.0526 0.6633 0.6394
0.250 0.2572 0.00718 0.00162 -0.0522 0.6303 0.6433
0.500 0.2836 0.00734 0.00164 -0.0517 0.5886 0.6475
0.750 0.3097 0.00757 0.00167 -0.0512 0.5413 0.6519
1.000 0.3347 0.00795 0.00175 -0.0506 0.4703 0.6561
1.250 0.3591 0.00841 0.00188 -0.0499 0.3883 0.6598
1.500 0.3832 0.00897 0.00206 -0.0493 0.2958 0.6638
1.750 0.4078 0.00950 0.00226 -0.0488 0.2149 0.6679
2.000 0.4333 0.00993 0.00243 -0.0485 0.1599 0.6720
2.250 0.4598 0.01021 0.00259 -0.0482 0.1332 0.6758
2.500 0.4864 0.01043 0.00274 -0.0479 0.1173 0.6793
2.750 0.5134 0.01062 0.00289 -0.0476 0.1081 0.6833
3.000 0.5404 0.01081 0.00306 -0.0474 0.1016 0.6876
3.250 0.5675 0.01099 0.00323 -0.0471 0.0967 0.6916
3.500 0.5941 0.01120 0.00342 -0.0468 0.0915 0.6952
3.750 0.6210 0.01137 0.00360 -0.0466 0.0879 0.6994
4.000 0.6478 0.01156 0.00380 -0.0463 0.0832 0.7041
4.250 0.6743 0.01179 0.00400 -0.0460 0.0784 0.7087
4.500 0.7010 0.01196 0.00419 -0.0457 0.0743 0.7129
4.750 0.7273 0.01218 0.00441 -0.0454 0.0703 0.7176
5.000 0.7539 0.01237 0.00462 -0.0451 0.0668 0.7231
5.250 0.7801 0.01259 0.00484 -0.0447 0.0632 0.7285
5.500 0.8062 0.01281 0.00510 -0.0444 0.0601 0.7345
5.750 0.8322 0.01304 0.00534 -0.0440 0.0566 0.7408
6.000 0.8579 0.01330 0.00561 -0.0436 0.0533 0.7472
6.250 0.8835 0.01354 0.00589 -0.0432 0.0499 0.7547
6.500 0.9089 0.01382 0.00620 -0.0427 0.0469 0.7634
6.750 0.9339 0.01409 0.00652 -0.0422 0.0441 0.7738
7.000 0.9585 0.01440 0.00687 -0.0417 0.0416 0.7857
7.250 0.9830 0.01468 0.00723 -0.0411 0.0391 0.8004
7.500 1.0066 0.01500 0.00761 -0.0403 0.0370 0.8205
7.750 1.0288 0.01522 0.00800 -0.0392 0.0351 0.8573
8.000 1.0554 0.01546 0.00839 -0.0390 0.0332 1.0000
8.250 1.0796 0.01589 0.00885 -0.0385 0.0317 1.0000
8.500 1.1036 0.01633 0.00931 -0.0379 0.0303 1.0000
8.750 1.1272 0.01682 0.00980 -0.0373 0.0292 1.0000
9.000 1.1502 0.01735 0.01036 -0.0366 0.0284 1.0000
9.250 1.1732 0.01786 0.01092 -0.0360 0.0277 1.0000
9.500 1.1958 0.01839 0.01150 -0.0352 0.0269 1.0000
9.750 1.2179 0.01895 0.01210 -0.0345 0.0263 1.0000
10.000 1.2395 0.01955 0.01274 -0.0336 0.0258 1.0000
10.250 1.2600 0.02023 0.01345 -0.0327 0.0252 1.0000
10.500 1.2798 0.02095 0.01422 -0.0317 0.0248 1.0000
10.750 1.3000 0.02161 0.01496 -0.0307 0.0244 1.0000
11.000 1.3195 0.02229 0.01572 -0.0296 0.0240 1.0000
11.250 1.3382 0.02301 0.01651 -0.0285 0.0236 1.0000
11.500 1.3560 0.02375 0.01733 -0.0273 0.0232 1.0000
11.750 1.3727 0.02455 0.01820 -0.0259 0.0229 1.0000
12.000 1.3881 0.02538 0.01910 -0.0244 0.0226 1.0000
12.250 1.4005 0.02624 0.02004 -0.0224 0.0223 1.0000
12.500 1.4106 0.02718 0.02104 -0.0202 0.0221 1.0000
12.750 1.4190 0.02823 0.02217 -0.0180 0.0219 1.0000
13.000 1.4253 0.02945 0.02346 -0.0157 0.0217 1.0000
13.250 1.4310 0.03078 0.02487 -0.0136 0.0215 1.0000
13.500 1.4379 0.03208 0.02630 -0.0118 0.0214 1.0000
13.750 1.4434 0.03353 0.02788 -0.0102 0.0213 1.0000
14.000 1.4477 0.03517 0.02965 -0.0087 0.0211 1.0000
14.250 1.4504 0.03701 0.03162 -0.0074 0.0210 1.0000
14.500 1.4524 0.03903 0.03377 -0.0064 0.0208 1.0000
14.750 1.4528 0.04133 0.03621 -0.0056 0.0207 1.0000
15.000 1.4513 0.04395 0.03897 -0.0052 0.0206 1.0000
15.250 1.4487 0.04686 0.04202 -0.0052 0.0205 1.0000
15.500 1.4444 0.05015 0.04546 -0.0056 0.0204 1.0000
15.750 1.4379 0.05392 0.04938 -0.0065 0.0203 1.0000
16.000 1.4292 0.05827 0.05389 -0.0080 0.0202 1.0000
16.250 1.4184 0.06323 0.05901 -0.0102 0.0201 1.0000
16.500 1.4045 0.06905 0.06499 -0.0131 0.0201 1.0000
16.750 1.3876 0.07587 0.07199 -0.0170 0.0200 1.0000
17.000 1.3661 0.08404 0.08035 -0.0220 0.0200 1.0000
17.250 1.3398 0.09378 0.09029 -0.0283 0.0200 1.0000
17.500 1.3052 0.10582 0.10255 -0.0360 0.0200 1.0000
17.750 1.2577 0.12143 0.11841 -0.0461 0.0201 1.0000
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