RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il) Reynolds number: 200,000 Max Cl/Cd: 49.64 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5213-il-200000.txt Download as CSV file: xf-rae5213-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5018 0.10520 0.10125 -0.0186 1.0000 0.0515
-10.000 -0.5160 0.09863 0.09475 -0.0253 1.0000 0.0535
-9.750 -0.5516 0.08785 0.08400 -0.0386 1.0000 0.0540
-9.500 -0.5187 0.08933 0.08552 -0.0290 1.0000 0.0550
-9.250 -0.5109 0.08690 0.08311 -0.0284 1.0000 0.0560
-9.000 -0.5098 0.08324 0.07950 -0.0298 1.0000 0.0576
-8.750 -0.5170 0.07793 0.07423 -0.0336 1.0000 0.0589
-8.500 -0.5359 0.07120 0.06753 -0.0397 1.0000 0.0592
-8.250 -0.5601 0.06585 0.06211 -0.0438 1.0000 0.0599
-7.750 -0.5908 0.05610 0.05192 -0.0466 1.0000 0.0632
-7.500 -0.5800 0.05354 0.04940 -0.0456 1.0000 0.0643
-7.250 -0.5722 0.05103 0.04685 -0.0447 1.0000 0.0663
-7.000 -0.5782 0.04753 0.04273 -0.0441 1.0000 0.0721
-6.750 -0.5647 0.04456 0.03990 -0.0431 1.0000 0.0735
-6.500 -0.5524 0.04259 0.03792 -0.0417 1.0000 0.0765
-6.250 -0.5449 0.03998 0.03499 -0.0406 1.0000 0.0841
-6.000 -0.5291 0.02918 0.02273 -0.0379 1.0000 0.0456
-5.750 -0.5105 0.02525 0.01789 -0.0359 1.0000 0.0413
-5.500 -0.4911 0.02341 0.01605 -0.0349 1.0000 0.0422
-5.250 -0.4714 0.02244 0.01507 -0.0338 1.0000 0.0442
-5.000 -0.4505 0.02113 0.01353 -0.0325 1.0000 0.0454
-4.750 -0.4289 0.01989 0.01209 -0.0313 1.0000 0.0462
-4.500 -0.4074 0.01879 0.01083 -0.0301 1.0000 0.0475
-4.250 -0.3865 0.01795 0.01009 -0.0292 1.0000 0.0500
-4.000 -0.3636 0.01733 0.00941 -0.0285 0.9997 0.0525
-3.750 -0.3258 0.01636 0.00844 -0.0305 0.9959 0.0551
-3.500 -0.2880 0.01570 0.00787 -0.0328 0.9914 0.0599
-3.250 -0.2498 0.01492 0.00714 -0.0351 0.9868 0.0643
-3.000 -0.2117 0.01440 0.00665 -0.0374 0.9818 0.0715
-2.750 -0.1731 0.01364 0.00599 -0.0399 0.9766 0.0852
-2.500 -0.1412 0.01113 0.00547 -0.0425 0.9728 0.5075
-2.250 -0.1066 0.01127 0.00584 -0.0433 0.9655 0.6117
-2.000 -0.0691 0.01147 0.00604 -0.0448 0.9596 0.6462
-1.750 -0.0332 0.01168 0.00627 -0.0459 0.9526 0.6765
-1.500 0.0054 0.01198 0.00668 -0.0469 0.9482 0.7118
-1.250 0.0340 0.01215 0.00696 -0.0460 0.9395 0.7362
-1.000 0.0752 0.01209 0.00690 -0.0482 0.9355 0.7491
-0.750 0.1082 0.01200 0.00678 -0.0490 0.9275 0.7558
-0.500 0.1485 0.01180 0.00653 -0.0512 0.9208 0.7626
-0.250 0.1816 0.01157 0.00633 -0.0516 0.9104 0.7678
0.000 0.2193 0.01129 0.00602 -0.0528 0.9017 0.7738
0.250 0.2487 0.01107 0.00577 -0.0524 0.8868 0.7801
0.500 0.2765 0.01076 0.00545 -0.0513 0.8682 0.7853
0.750 0.3035 0.01054 0.00518 -0.0501 0.8481 0.7916
1.000 0.3300 0.01040 0.00500 -0.0492 0.8289 0.7977
1.250 0.3559 0.01028 0.00488 -0.0482 0.8110 0.8035
1.500 0.3822 0.01020 0.00478 -0.0474 0.7911 0.8102
1.750 0.4080 0.01013 0.00469 -0.0465 0.7686 0.8163
2.000 0.4334 0.01007 0.00460 -0.0454 0.7435 0.8230
2.250 0.4592 0.01007 0.00453 -0.0445 0.7123 0.8304
2.500 0.4829 0.01006 0.00445 -0.0430 0.6718 0.8372
2.750 0.5058 0.01019 0.00437 -0.0415 0.6053 0.8457
3.000 0.5214 0.01083 0.00433 -0.0387 0.4538 0.8540
3.250 0.5321 0.01247 0.00480 -0.0362 0.2312 0.8644
3.500 0.5513 0.01320 0.00521 -0.0347 0.1802 0.8757
3.750 0.5729 0.01370 0.00560 -0.0335 0.1617 0.8895
4.000 0.5963 0.01407 0.00597 -0.0326 0.1498 0.9078
4.250 0.6236 0.01450 0.00643 -0.0325 0.1399 0.9379
4.500 0.6576 0.01525 0.00707 -0.0343 0.1302 1.0000
4.750 0.6868 0.01572 0.00753 -0.0349 0.1226 1.0000
5.000 0.7134 0.01656 0.00824 -0.0352 0.1154 1.0000
5.250 0.7410 0.01702 0.00872 -0.0353 0.1086 1.0000
5.500 0.7667 0.01799 0.00953 -0.0353 0.1023 1.0000
5.750 0.7934 0.01846 0.01008 -0.0351 0.0966 1.0000
6.000 0.8188 0.01939 0.01086 -0.0350 0.0911 1.0000
6.250 0.8447 0.02004 0.01162 -0.0347 0.0859 1.0000
6.500 0.8698 0.02070 0.01221 -0.0344 0.0810 1.0000
6.750 0.8951 0.02174 0.01332 -0.0341 0.0765 1.0000
7.000 0.9200 0.02243 0.01404 -0.0337 0.0724 1.0000
7.250 0.9448 0.02361 0.01518 -0.0334 0.0690 1.0000
7.500 0.9690 0.02440 0.01613 -0.0328 0.0655 1.0000
7.750 0.9932 0.02519 0.01691 -0.0324 0.0629 1.0000
8.000 1.0172 0.02673 0.01852 -0.0319 0.0609 1.0000
8.250 1.0397 0.02821 0.02028 -0.0311 0.0589 1.0000
8.500 1.0622 0.02956 0.02178 -0.0304 0.0571 1.0000
8.750 1.0847 0.03063 0.02289 -0.0299 0.0556 1.0000
9.000 1.1063 0.03252 0.02479 -0.0295 0.0543 1.0000
9.250 1.1213 0.03477 0.02753 -0.0279 0.0531 1.0000
9.500 1.1343 0.03762 0.03081 -0.0263 0.0523 1.0000
9.750 1.1435 0.04090 0.03451 -0.0245 0.0518 1.0000
10.000 1.1473 0.04474 0.03879 -0.0224 0.0515 1.0000
10.250 1.1431 0.04933 0.04383 -0.0200 0.0516 1.0000
10.500 1.1314 0.05429 0.04920 -0.0175 0.0519 1.0000
10.750 1.1104 0.05938 0.05465 -0.0147 0.0523 1.0000
11.000 1.0851 0.06366 0.05916 -0.0118 0.0527 1.0000
11.250 1.0594 0.06825 0.06392 -0.0106 0.0531 1.0000
11.500 1.0344 0.07342 0.06925 -0.0113 0.0535 1.0000
11.750 1.0132 0.07910 0.07503 -0.0133 0.0538 1.0000
12.000 1.0003 0.08464 0.08063 -0.0157 0.0541 1.0000
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Polar data table (+)
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