RAE 5215 AIRFOIL (rae5215-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 5215 AIRFOIL (rae5215-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.2 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5215-il-1000000.txt Download as CSV file: xf-rae5215-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 5215 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4561 0.11259 0.11090 -0.0124 1.0000 0.0154
-11.250 -0.4565 0.10861 0.10693 -0.0136 1.0000 0.0156
-11.000 -0.9500 0.03134 0.02789 -0.0515 1.0000 0.0099
-10.750 -0.9406 0.02825 0.02449 -0.0516 1.0000 0.0099
-10.500 -0.9274 0.02550 0.02143 -0.0516 1.0000 0.0099
-10.250 -0.9110 0.02312 0.01879 -0.0514 1.0000 0.0099
-10.000 -0.8923 0.02111 0.01655 -0.0512 1.0000 0.0100
-9.750 -0.8712 0.01961 0.01489 -0.0510 1.0000 0.0101
-9.500 -0.8484 0.01850 0.01368 -0.0508 1.0000 0.0103
-9.250 -0.8248 0.01766 0.01275 -0.0505 1.0000 0.0104
-9.000 -0.8009 0.01692 0.01195 -0.0502 1.0000 0.0106
-8.750 -0.7771 0.01626 0.01123 -0.0498 1.0000 0.0108
-8.500 -0.7535 0.01563 0.01054 -0.0493 1.0000 0.0110
-8.250 -0.7302 0.01500 0.00985 -0.0486 1.0000 0.0113
-8.000 -0.7074 0.01442 0.00920 -0.0479 1.0000 0.0117
-7.750 -0.6852 0.01395 0.00865 -0.0470 1.0000 0.0120
-7.500 -0.6614 0.01324 0.00790 -0.0465 0.9997 0.0126
-7.250 -0.6278 0.01291 0.00759 -0.0479 0.9983 0.0132
-7.000 -0.5941 0.01258 0.00722 -0.0493 0.9968 0.0140
-6.750 -0.5599 0.01230 0.00688 -0.0508 0.9954 0.0147
-6.500 -0.5261 0.01168 0.00626 -0.0523 0.9942 0.0156
-6.250 -0.4929 0.01137 0.00596 -0.0536 0.9918 0.0164
-6.000 -0.4589 0.01107 0.00562 -0.0550 0.9896 0.0173
-5.750 -0.4252 0.01054 0.00508 -0.0564 0.9873 0.0183
-5.500 -0.3913 0.01022 0.00477 -0.0578 0.9850 0.0193
-5.250 -0.3598 0.00997 0.00449 -0.0586 0.9802 0.0204
-5.000 -0.3284 0.00953 0.00405 -0.0594 0.9755 0.0216
-4.750 -0.2982 0.00926 0.00378 -0.0599 0.9698 0.0228
-4.500 -0.2696 0.00905 0.00355 -0.0600 0.9627 0.0239
-4.250 -0.2417 0.00874 0.00323 -0.0599 0.9554 0.0250
-4.000 -0.2142 0.00853 0.00301 -0.0597 0.9478 0.0264
-3.750 -0.1865 0.00837 0.00283 -0.0595 0.9404 0.0277
-3.500 -0.1589 0.00814 0.00260 -0.0593 0.9326 0.0298
-3.250 -0.1312 0.00800 0.00244 -0.0591 0.9247 0.0319
-3.000 -0.1038 0.00781 0.00226 -0.0588 0.9146 0.0349
-2.750 -0.0757 0.00764 0.00209 -0.0587 0.9049 0.0402
-2.500 -0.0478 0.00738 0.00191 -0.0586 0.8951 0.0666
-2.250 -0.0186 0.00682 0.00171 -0.0591 0.8876 0.1649
-2.000 0.0105 0.00593 0.00147 -0.0600 0.8803 0.3611
-1.750 0.0390 0.00542 0.00136 -0.0603 0.8680 0.4914
-1.500 0.0668 0.00532 0.00133 -0.0600 0.8499 0.5409
-1.250 0.0950 0.00531 0.00130 -0.0598 0.8323 0.5665
-1.000 0.1234 0.00533 0.00129 -0.0596 0.8166 0.5853
-0.750 0.1520 0.00536 0.00131 -0.0595 0.8030 0.6044
-0.500 0.1807 0.00541 0.00135 -0.0594 0.7884 0.6222
-0.250 0.2092 0.00547 0.00139 -0.0593 0.7710 0.6360
0.000 0.2376 0.00554 0.00142 -0.0592 0.7501 0.6464
0.250 0.2661 0.00563 0.00142 -0.0591 0.7205 0.6511
0.500 0.2936 0.00586 0.00142 -0.0588 0.6597 0.6549
0.750 0.3182 0.00670 0.00156 -0.0583 0.4832 0.6585
1.000 0.3431 0.00753 0.00176 -0.0581 0.3167 0.6625
1.250 0.3694 0.00814 0.00194 -0.0580 0.2073 0.6664
1.500 0.3968 0.00851 0.00207 -0.0579 0.1544 0.6704
1.750 0.4249 0.00872 0.00218 -0.0579 0.1361 0.6740
2.000 0.4532 0.00885 0.00228 -0.0579 0.1273 0.6781
2.250 0.4815 0.00899 0.00240 -0.0579 0.1205 0.6822
2.500 0.5098 0.00911 0.00251 -0.0578 0.1162 0.6862
2.750 0.5380 0.00928 0.00264 -0.0578 0.1111 0.6901
3.000 0.5661 0.00944 0.00279 -0.0578 0.1067 0.6938
3.250 0.5944 0.00952 0.00290 -0.0578 0.1031 0.6981
3.500 0.6224 0.00967 0.00302 -0.0577 0.0979 0.7023
3.750 0.6504 0.00983 0.00317 -0.0577 0.0937 0.7066
4.000 0.6786 0.00995 0.00328 -0.0577 0.0902 0.7106
4.250 0.7063 0.01010 0.00343 -0.0576 0.0857 0.7153
4.500 0.7342 0.01024 0.00358 -0.0575 0.0822 0.7201
4.750 0.7620 0.01039 0.00373 -0.0574 0.0781 0.7251
5.000 0.7896 0.01058 0.00390 -0.0573 0.0735 0.7303
5.250 0.8172 0.01072 0.00405 -0.0573 0.0692 0.7360
5.500 0.8446 0.01092 0.00424 -0.0571 0.0645 0.7419
5.750 0.8718 0.01112 0.00443 -0.0570 0.0599 0.7480
6.000 0.8989 0.01132 0.00466 -0.0568 0.0559 0.7556
6.250 0.9256 0.01160 0.00492 -0.0566 0.0517 0.7637
6.500 0.9524 0.01182 0.00517 -0.0564 0.0480 0.7735
6.750 0.9789 0.01209 0.00547 -0.0561 0.0443 0.7846
7.000 1.0047 0.01243 0.00583 -0.0558 0.0405 0.7989
7.250 1.0309 0.01265 0.00614 -0.0555 0.0379 0.8198
7.500 1.0552 0.01292 0.00654 -0.0548 0.0354 0.8621
7.750 1.0766 0.01294 0.00678 -0.0532 0.0336 1.0000
8.000 1.1023 0.01337 0.00719 -0.0529 0.0319 1.0000
8.250 1.1281 0.01378 0.00761 -0.0526 0.0307 1.0000
8.500 1.1540 0.01415 0.00801 -0.0523 0.0298 1.0000
8.750 1.1794 0.01457 0.00843 -0.0519 0.0289 1.0000
9.000 1.2039 0.01511 0.00899 -0.0515 0.0280 1.0000
9.250 1.2281 0.01567 0.00959 -0.0509 0.0273 1.0000
9.500 1.2529 0.01612 0.01008 -0.0505 0.0268 1.0000
9.750 1.2773 0.01659 0.01060 -0.0500 0.0263 1.0000
10.000 1.3014 0.01709 0.01113 -0.0494 0.0258 1.0000
10.250 1.3252 0.01760 0.01168 -0.0489 0.0253 1.0000
10.500 1.3481 0.01820 0.01231 -0.0482 0.0248 1.0000
10.750 1.3694 0.01898 0.01313 -0.0473 0.0244 1.0000
11.000 1.3885 0.02000 0.01422 -0.0462 0.0239 1.0000
11.250 1.4106 0.02060 0.01489 -0.0454 0.0238 1.0000
11.500 1.4320 0.02124 0.01560 -0.0445 0.0235 1.0000
11.750 1.4526 0.02194 0.01638 -0.0436 0.0233 1.0000
12.000 1.4724 0.02269 0.01721 -0.0425 0.0231 1.0000
12.250 1.4913 0.02348 0.01807 -0.0414 0.0228 1.0000
12.500 1.5094 0.02430 0.01898 -0.0402 0.0226 1.0000
12.750 1.5265 0.02517 0.01992 -0.0388 0.0223 1.0000
13.000 1.5424 0.02607 0.02090 -0.0373 0.0221 1.0000
13.250 1.5569 0.02702 0.02193 -0.0357 0.0219 1.0000
13.500 1.5693 0.02802 0.02300 -0.0338 0.0217 1.0000
13.750 1.5774 0.02908 0.02414 -0.0313 0.0216 1.0000
14.000 1.5830 0.03028 0.02542 -0.0286 0.0214 1.0000
14.250 1.5869 0.03168 0.02691 -0.0260 0.0213 1.0000
14.500 1.5885 0.03335 0.02868 -0.0235 0.0211 1.0000
14.750 1.5870 0.03539 0.03083 -0.0211 0.0210 1.0000
15.000 1.5817 0.03794 0.03352 -0.0189 0.0208 1.0000
15.250 1.5724 0.04107 0.03680 -0.0171 0.0207 1.0000
15.500 1.5685 0.04380 0.03967 -0.0160 0.0207 1.0000
15.750 1.5660 0.04655 0.04256 -0.0155 0.0206 1.0000
16.000 1.5604 0.04983 0.04598 -0.0153 0.0206 1.0000
16.250 1.5526 0.05364 0.04994 -0.0158 0.0205 1.0000
16.500 1.5424 0.05806 0.05451 -0.0170 0.0205 1.0000
16.750 1.5286 0.06340 0.06000 -0.0190 0.0205 1.0000
17.000 1.5112 0.06985 0.06662 -0.0223 0.0204 1.0000
17.250 1.4893 0.07769 0.07464 -0.0269 0.0204 1.0000
17.500 1.4622 0.08717 0.08430 -0.0328 0.0204 1.0000
17.750 1.4285 0.09832 0.09565 -0.0398 0.0205 1.0000
18.000 1.3875 0.11113 0.10864 -0.0476 0.0205 1.0000
18.250 1.3396 0.12555 0.12324 -0.0564 0.0206 1.0000
18.500 1.2757 0.14439 0.14231 -0.0683 0.0206 1.0000
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