RAE(NPL) 5212 AIRFOIL (rae5212-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE(NPL) 5212 AIRFOIL (rae5212-il) Reynolds number: 500,000 Max Cl/Cd: 69.77 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5212-il-500000.txt Download as CSV file: xf-rae5212-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3948 0.09508 0.09278 -0.0413 1.0000 0.0303
-11.000 -0.7109 0.05244 0.04935 -0.0661 1.0000 0.0192
-10.750 -0.7318 0.04962 0.04646 -0.0645 1.0000 0.0191
-10.500 -0.7553 0.04781 0.04460 -0.0609 1.0000 0.0190
-10.250 -0.7779 0.04576 0.04244 -0.0562 1.0000 0.0190
-10.000 -0.7960 0.04299 0.03951 -0.0523 1.0000 0.0188
-9.750 -0.8179 0.03925 0.03545 -0.0478 1.0000 0.0190
-9.500 -0.8179 0.03486 0.03061 -0.0470 0.9983 0.0190
-9.250 -0.7981 0.03063 0.02582 -0.0490 0.9951 0.0192
-9.000 -0.7749 0.02759 0.02231 -0.0503 0.9920 0.0195
-8.750 -0.7505 0.02471 0.01920 -0.0514 0.9891 0.0200
-8.500 -0.7204 0.02334 0.01774 -0.0528 0.9869 0.0204
-8.250 -0.6881 0.02238 0.01670 -0.0545 0.9851 0.0211
-8.000 -0.6552 0.02119 0.01537 -0.0562 0.9838 0.0217
-7.750 -0.6289 0.02014 0.01419 -0.0563 0.9795 0.0225
-7.500 -0.5966 0.01949 0.01335 -0.0575 0.9767 0.0234
-7.250 -0.5659 0.01793 0.01175 -0.0588 0.9747 0.0243
-7.000 -0.5320 0.01716 0.01099 -0.0604 0.9732 0.0253
-6.750 -0.4997 0.01648 0.01026 -0.0617 0.9711 0.0263
-6.500 -0.4737 0.01582 0.00955 -0.0615 0.9658 0.0273
-6.250 -0.4415 0.01506 0.00873 -0.0627 0.9631 0.0285
-6.000 -0.4077 0.01433 0.00804 -0.0644 0.9612 0.0304
-5.750 -0.3719 0.01380 0.00748 -0.0663 0.9599 0.0323
-5.500 -0.3457 0.01333 0.00697 -0.0660 0.9545 0.0339
-5.250 -0.3152 0.01261 0.00628 -0.0670 0.9510 0.0364
-5.000 -0.2797 0.01221 0.00586 -0.0687 0.9490 0.0395
-4.750 -0.2448 0.01161 0.00528 -0.0704 0.9472 0.0437
-4.500 -0.2094 0.01118 0.00484 -0.0721 0.9455 0.0491
-4.250 -0.1855 0.01079 0.00447 -0.0713 0.9383 0.0563
-4.000 -0.1543 0.01026 0.00401 -0.0721 0.9345 0.0727
-3.750 -0.1228 0.00948 0.00355 -0.0733 0.9315 0.1428
-3.500 -0.1034 0.00822 0.00305 -0.0725 0.9237 0.3333
-3.250 -0.0771 0.00740 0.00283 -0.0726 0.9185 0.4972
-3.000 -0.0460 0.00728 0.00278 -0.0730 0.9140 0.5466
-2.750 -0.0181 0.00725 0.00274 -0.0728 0.9069 0.5696
-2.500 0.0135 0.00721 0.00268 -0.0734 0.9020 0.5864
-2.250 0.0421 0.00725 0.00269 -0.0733 0.8952 0.6016
-2.000 0.0712 0.00730 0.00274 -0.0732 0.8887 0.6160
-1.750 0.1012 0.00739 0.00283 -0.0734 0.8829 0.6302
-1.500 0.1281 0.00748 0.00293 -0.0729 0.8752 0.6420
-1.250 0.1582 0.00758 0.00295 -0.0731 0.8691 0.6513
-1.000 0.1850 0.00755 0.00294 -0.0726 0.8604 0.6558
-0.750 0.2145 0.00755 0.00288 -0.0728 0.8525 0.6595
-0.500 0.2408 0.00753 0.00282 -0.0722 0.8402 0.6632
-0.250 0.2675 0.00753 0.00273 -0.0716 0.8252 0.6668
0.000 0.2942 0.00748 0.00265 -0.0711 0.8106 0.6699
0.250 0.3212 0.00747 0.00261 -0.0707 0.7980 0.6730
0.500 0.3476 0.00748 0.00256 -0.0701 0.7819 0.6764
0.750 0.3741 0.00750 0.00252 -0.0696 0.7661 0.6800
1.000 0.4011 0.00754 0.00250 -0.0693 0.7530 0.6834
1.250 0.4276 0.00754 0.00248 -0.0689 0.7393 0.6865
1.500 0.4538 0.00757 0.00249 -0.0683 0.7235 0.6897
1.750 0.4797 0.00763 0.00251 -0.0678 0.7051 0.6932
2.000 0.5052 0.00770 0.00253 -0.0671 0.6824 0.6970
2.250 0.5300 0.00781 0.00254 -0.0663 0.6556 0.7005
2.500 0.5533 0.00793 0.00257 -0.0652 0.6169 0.7039
2.750 0.5731 0.00825 0.00265 -0.0635 0.5525 0.7077
3.000 0.5893 0.00886 0.00284 -0.0612 0.4615 0.7118
3.250 0.6057 0.00958 0.00312 -0.0591 0.3680 0.7159
3.500 0.6233 0.01023 0.00340 -0.0573 0.2827 0.7198
3.750 0.6416 0.01091 0.00373 -0.0557 0.2061 0.7240
4.250 0.6828 0.01201 0.00434 -0.0533 0.1174 0.7330
4.500 0.7060 0.01230 0.00461 -0.0524 0.1064 0.7374
4.750 0.7290 0.01262 0.00492 -0.0515 0.0993 0.7426
5.000 0.7532 0.01287 0.00518 -0.0508 0.0951 0.7480
5.250 0.7761 0.01316 0.00548 -0.0499 0.0914 0.7531
5.500 0.7973 0.01359 0.00593 -0.0487 0.0876 0.7590
5.750 0.8212 0.01383 0.00621 -0.0480 0.0859 0.7653
6.000 0.8442 0.01406 0.00651 -0.0471 0.0837 0.7720
6.250 0.8669 0.01436 0.00685 -0.0462 0.0815 0.7803
6.500 0.8883 0.01468 0.00723 -0.0450 0.0795 0.7895
6.750 0.9080 0.01515 0.00775 -0.0436 0.0773 0.8007
7.000 0.9258 0.01577 0.00846 -0.0419 0.0753 0.8154
7.250 0.9466 0.01598 0.00882 -0.0405 0.0744 0.8386
7.500 0.9671 0.01610 0.00923 -0.0391 0.0732 0.9130
7.750 1.0016 0.01657 0.00977 -0.0409 0.0715 1.0000
8.000 1.0235 0.01701 0.01022 -0.0400 0.0698 1.0000
8.250 1.0447 0.01748 0.01069 -0.0390 0.0683 1.0000
8.500 1.0648 0.01806 0.01126 -0.0378 0.0669 1.0000
8.750 1.0845 0.01905 0.01224 -0.0368 0.0651 1.0000
9.000 1.1067 0.02010 0.01335 -0.0361 0.0639 1.0000
9.250 1.1273 0.02052 0.01383 -0.0350 0.0632 1.0000
9.500 1.1474 0.02099 0.01436 -0.0338 0.0622 1.0000
9.750 1.1668 0.02149 0.01493 -0.0325 0.0610 1.0000
10.000 1.1853 0.02199 0.01547 -0.0311 0.0597 1.0000
10.250 1.2032 0.02249 0.01601 -0.0297 0.0585 1.0000
10.500 1.2199 0.02292 0.01645 -0.0281 0.0572 1.0000
10.750 1.2372 0.02358 0.01712 -0.0267 0.0559 1.0000
11.000 1.2602 0.02533 0.01893 -0.0267 0.0542 1.0000
11.250 1.2746 0.02571 0.01940 -0.0247 0.0536 1.0000
11.500 1.2886 0.02610 0.01988 -0.0227 0.0527 1.0000
11.750 1.3026 0.02661 0.02048 -0.0209 0.0516 1.0000
12.000 1.3164 0.02719 0.02114 -0.0191 0.0505 1.0000
12.250 1.3294 0.02771 0.02172 -0.0173 0.0495 1.0000
12.500 1.3421 0.02827 0.02232 -0.0156 0.0485 1.0000
12.750 1.3546 0.02896 0.02302 -0.0140 0.0476 1.0000
13.000 1.3665 0.03019 0.02429 -0.0125 0.0464 1.0000
13.250 1.3768 0.03132 0.02555 -0.0108 0.0455 1.0000
13.500 1.3866 0.03211 0.02646 -0.0091 0.0448 1.0000
13.750 1.3959 0.03300 0.02747 -0.0075 0.0438 1.0000
14.000 1.4052 0.03384 0.02839 -0.0060 0.0427 1.0000
14.250 1.4145 0.03476 0.02937 -0.0046 0.0417 1.0000
14.500 1.4241 0.03557 0.03022 -0.0035 0.0407 1.0000
14.750 1.4313 0.03686 0.03152 -0.0023 0.0398 1.0000
15.000 1.4350 0.03872 0.03347 -0.0011 0.0387 1.0000
15.250 1.4416 0.04011 0.03503 -0.0001 0.0378 1.0000
15.500 1.4478 0.04166 0.03670 0.0006 0.0367 1.0000
15.750 1.4548 0.04314 0.03824 0.0012 0.0355 1.0000
16.000 1.4612 0.04474 0.03989 0.0016 0.0345 1.0000
16.250 1.4622 0.04703 0.04221 0.0020 0.0336 1.0000
16.500 1.4598 0.04987 0.04518 0.0022 0.0326 1.0000
16.750 1.4613 0.05241 0.04788 0.0021 0.0316 1.0000
17.000 1.4602 0.05535 0.05095 0.0018 0.0308 1.0000
17.250 1.4600 0.05830 0.05400 0.0012 0.0299 1.0000
17.500 1.4569 0.06180 0.05758 0.0003 0.0292 1.0000
17.750 1.4499 0.06599 0.06184 -0.0012 0.0285 1.0000
18.000 1.4360 0.07133 0.06728 -0.0032 0.0279 1.0000
18.250 1.4252 0.07668 0.07281 -0.0056 0.0274 1.0000
18.500 1.4118 0.08270 0.07901 -0.0086 0.0270 1.0000
18.750 1.3969 0.08926 0.08575 -0.0122 0.0265 1.0000
19.000 1.3773 0.09688 0.09354 -0.0165 0.0262 1.0000
19.250 1.3545 0.10542 0.10225 -0.0215 0.0260 1.0000
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