RAE 5214 AIRFOIL (rae5214-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 5214 AIRFOIL (rae5214-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.71 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5214-il-1000000-n5.txt Download as CSV file: xf-rae5214-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE 5214 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -1.0587 0.06257 0.05984 -0.0454 1.0000 0.0062
-15.250 -1.0970 0.05213 0.04916 -0.0531 1.0000 0.0062
-15.000 -1.1158 0.04614 0.04300 -0.0569 1.0000 0.0062
-14.750 -1.1290 0.04146 0.03816 -0.0594 1.0000 0.0062
-14.500 -1.1397 0.03746 0.03400 -0.0612 1.0000 0.0061
-14.250 -1.1420 0.03467 0.03109 -0.0619 1.0000 0.0062
-14.000 -1.1442 0.03213 0.02842 -0.0623 1.0000 0.0062
-13.750 -1.1466 0.02991 0.02607 -0.0620 1.0000 0.0063
-13.500 -1.1488 0.02826 0.02431 -0.0604 1.0000 0.0063
-13.250 -1.1421 0.02685 0.02277 -0.0591 1.0000 0.0063
-13.000 -1.1314 0.02555 0.02137 -0.0581 1.0000 0.0064
-12.750 -1.1181 0.02439 0.02009 -0.0571 1.0000 0.0065
-12.500 -1.1032 0.02331 0.01890 -0.0562 1.0000 0.0065
-12.250 -1.0869 0.02231 0.01780 -0.0552 1.0000 0.0066
-12.000 -1.0697 0.02136 0.01676 -0.0543 1.0000 0.0067
-11.750 -1.0516 0.02049 0.01579 -0.0534 1.0000 0.0068
-11.500 -1.0329 0.01968 0.01490 -0.0524 1.0000 0.0068
-11.250 -1.0136 0.01892 0.01406 -0.0515 1.0000 0.0069
-11.000 -0.9938 0.01822 0.01327 -0.0506 1.0000 0.0070
-10.750 -0.9736 0.01758 0.01256 -0.0496 1.0000 0.0071
-10.500 -0.9531 0.01697 0.01188 -0.0486 1.0000 0.0072
-10.250 -0.9334 0.01625 0.01110 -0.0476 1.0000 0.0075
-10.000 -0.9128 0.01569 0.01050 -0.0465 1.0000 0.0077
-9.750 -0.8840 0.01514 0.00991 -0.0472 0.9988 0.0079
-9.500 -0.8536 0.01462 0.00935 -0.0481 0.9971 0.0081
-9.250 -0.8230 0.01413 0.00882 -0.0490 0.9952 0.0085
-9.000 -0.7929 0.01365 0.00830 -0.0498 0.9932 0.0088
-8.750 -0.7629 0.01320 0.00779 -0.0505 0.9909 0.0091
-8.500 -0.7322 0.01277 0.00733 -0.0514 0.9888 0.0094
-8.250 -0.7009 0.01235 0.00690 -0.0523 0.9871 0.0099
-8.000 -0.6688 0.01200 0.00654 -0.0534 0.9857 0.0103
-7.750 -0.6378 0.01167 0.00619 -0.0542 0.9833 0.0108
-7.500 -0.6080 0.01134 0.00583 -0.0547 0.9795 0.0113
-7.250 -0.5769 0.01101 0.00549 -0.0555 0.9766 0.0118
-6.750 -0.5172 0.01049 0.00496 -0.0565 0.9677 0.0130
-6.500 -0.4867 0.01022 0.00467 -0.0570 0.9627 0.0137
-6.250 -0.4579 0.00998 0.00440 -0.0572 0.9563 0.0142
-6.000 -0.4284 0.00971 0.00414 -0.0576 0.9503 0.0149
-5.750 -0.4000 0.00950 0.00391 -0.0576 0.9432 0.0156
-5.500 -0.3716 0.00930 0.00369 -0.0576 0.9357 0.0164
-5.250 -0.3439 0.00912 0.00348 -0.0575 0.9277 0.0170
-5.000 -0.3165 0.00889 0.00323 -0.0573 0.9192 0.0177
-4.750 -0.2891 0.00871 0.00304 -0.0571 0.9106 0.0186
-4.250 -0.2341 0.00840 0.00267 -0.0567 0.8938 0.0205
-4.000 -0.2067 0.00823 0.00249 -0.0565 0.8854 0.0217
-3.750 -0.1790 0.00809 0.00232 -0.0564 0.8777 0.0228
-3.500 -0.1513 0.00795 0.00216 -0.0562 0.8697 0.0236
-3.250 -0.1236 0.00780 0.00200 -0.0560 0.8627 0.0251
-3.000 -0.0957 0.00767 0.00186 -0.0559 0.8541 0.0268
-2.750 -0.0684 0.00756 0.00173 -0.0556 0.8407 0.0296
-2.500 -0.0412 0.00746 0.00160 -0.0553 0.8238 0.0358
-2.250 -0.0142 0.00734 0.00148 -0.0549 0.8043 0.0514
-2.000 0.0126 0.00724 0.00137 -0.0545 0.7807 0.0696
-1.750 0.0395 0.00707 0.00126 -0.0543 0.7602 0.1086
-1.500 0.0664 0.00682 0.00115 -0.0541 0.7412 0.1692
-1.250 0.0927 0.00646 0.00102 -0.0539 0.7149 0.2703
-1.000 0.1177 0.00601 0.00088 -0.0536 0.6743 0.4140
-0.750 0.1424 0.00590 0.00087 -0.0531 0.6122 0.5164
-0.500 0.1677 0.00609 0.00094 -0.0525 0.5446 0.5627
-0.250 0.1934 0.00637 0.00104 -0.0520 0.4766 0.5876
0.250 0.2448 0.00709 0.00124 -0.0511 0.3261 0.6114
0.500 0.2708 0.00745 0.00134 -0.0508 0.2567 0.6156
0.750 0.2974 0.00776 0.00144 -0.0505 0.2057 0.6193
1.000 0.3245 0.00797 0.00152 -0.0502 0.1755 0.6230
1.250 0.3519 0.00813 0.00160 -0.0500 0.1556 0.6271
1.500 0.3794 0.00828 0.00169 -0.0498 0.1396 0.6312
1.750 0.4070 0.00844 0.00177 -0.0497 0.1251 0.6352
2.250 0.4620 0.00872 0.00196 -0.0493 0.1053 0.6426
2.500 0.4896 0.00885 0.00207 -0.0491 0.0991 0.6463
2.750 0.5172 0.00898 0.00218 -0.0489 0.0945 0.6502
3.000 0.5445 0.00914 0.00231 -0.0487 0.0891 0.6538
3.500 0.5993 0.00943 0.00255 -0.0483 0.0802 0.6605
3.750 0.6266 0.00957 0.00269 -0.0481 0.0756 0.6643
4.000 0.6538 0.00972 0.00283 -0.0479 0.0712 0.6680
4.250 0.6810 0.00989 0.00298 -0.0476 0.0678 0.6715
4.750 0.7350 0.01023 0.00330 -0.0471 0.0602 0.6788
5.000 0.7618 0.01041 0.00347 -0.0469 0.0561 0.6829
5.250 0.7886 0.01061 0.00366 -0.0466 0.0526 0.6869
5.500 0.8152 0.01082 0.00386 -0.0463 0.0492 0.6906
5.750 0.8417 0.01102 0.00407 -0.0460 0.0464 0.6946
6.000 0.8680 0.01124 0.00429 -0.0457 0.0435 0.6994
6.250 0.8943 0.01147 0.00453 -0.0453 0.0409 0.7045
6.500 0.9204 0.01172 0.00478 -0.0450 0.0381 0.7091
6.750 0.9464 0.01196 0.00504 -0.0446 0.0357 0.7141
7.000 0.9721 0.01223 0.00532 -0.0442 0.0329 0.7198
7.250 0.9979 0.01250 0.00561 -0.0438 0.0307 0.7257
7.500 1.0232 0.01281 0.00593 -0.0433 0.0285 0.7327
7.750 1.0486 0.01308 0.00624 -0.0429 0.0272 0.7411
8.000 1.0737 0.01339 0.00658 -0.0424 0.0260 0.7498
8.250 1.0984 0.01373 0.00696 -0.0419 0.0249 0.7602
8.500 1.1233 0.01402 0.00732 -0.0414 0.0243 0.7720
8.750 1.1479 0.01433 0.00769 -0.0408 0.0236 0.7867
9.000 1.1720 0.01464 0.00809 -0.0402 0.0230 0.8077
9.250 1.1948 0.01491 0.00851 -0.0393 0.0225 0.8485
9.500 1.2187 0.01510 0.00894 -0.0386 0.0219 1.0000
9.750 1.2424 0.01556 0.00943 -0.0380 0.0214 1.0000
10.000 1.2663 0.01596 0.00986 -0.0374 0.0210 1.0000
10.250 1.2899 0.01639 0.01033 -0.0368 0.0207 1.0000
10.500 1.3131 0.01684 0.01082 -0.0361 0.0204 1.0000
10.750 1.3359 0.01731 0.01134 -0.0354 0.0201 1.0000
11.000 1.3583 0.01780 0.01187 -0.0347 0.0198 1.0000
11.250 1.3802 0.01833 0.01244 -0.0339 0.0195 1.0000
11.500 1.4016 0.01888 0.01303 -0.0330 0.0192 1.0000
11.750 1.4223 0.01948 0.01367 -0.0321 0.0190 1.0000
12.000 1.4421 0.02013 0.01438 -0.0310 0.0187 1.0000
12.250 1.4605 0.02089 0.01519 -0.0298 0.0185 1.0000
12.500 1.4795 0.02153 0.01589 -0.0287 0.0183 1.0000
12.750 1.4979 0.02217 0.01661 -0.0275 0.0182 1.0000
13.000 1.5155 0.02284 0.01735 -0.0262 0.0181 1.0000
13.250 1.5317 0.02356 0.01815 -0.0247 0.0180 1.0000
13.500 1.5461 0.02428 0.01895 -0.0230 0.0178 1.0000
13.750 1.5573 0.02505 0.01979 -0.0207 0.0177 1.0000
14.000 1.5671 0.02587 0.02070 -0.0184 0.0176 1.0000
14.250 1.5763 0.02676 0.02166 -0.0161 0.0174 1.0000
14.500 1.5842 0.02775 0.02273 -0.0139 0.0173 1.0000
14.750 1.5911 0.02884 0.02392 -0.0118 0.0172 1.0000
15.000 1.5972 0.03005 0.02522 -0.0098 0.0171 1.0000
15.250 1.6020 0.03141 0.02667 -0.0080 0.0170 1.0000
15.500 1.6058 0.03293 0.02829 -0.0063 0.0169 1.0000
15.750 1.6085 0.03462 0.03008 -0.0049 0.0168 1.0000
16.000 1.6096 0.03656 0.03212 -0.0036 0.0167 1.0000
16.250 1.6091 0.03876 0.03442 -0.0027 0.0166 1.0000
16.500 1.6071 0.04127 0.03704 -0.0021 0.0165 1.0000
16.750 1.6025 0.04425 0.04013 -0.0019 0.0165 1.0000
17.000 1.5963 0.04764 0.04365 -0.0023 0.0164 1.0000
17.250 1.5885 0.05151 0.04763 -0.0033 0.0162 1.0000
17.500 1.5728 0.05681 0.05310 -0.0053 0.0163 1.0000
17.750 1.5552 0.06305 0.05948 -0.0085 0.0163 1.0000
18.000 1.5298 0.07134 0.06797 -0.0134 0.0163 1.0000
18.250 1.4905 0.08332 0.08018 -0.0212 0.0163 1.0000
18.500 1.4242 0.10181 0.09897 -0.0330 0.0164 1.0000
18.750 1.3466 0.12280 0.12023 -0.0463 0.0165 1.0000
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Polar data table (+)
Polar graphs
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