RAF 31 AIRFOIL (raf31-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 31 AIRFOIL (raf31-il) Reynolds number: 200,000 Max Cl/Cd: 65.05 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf31-il-200000-n5.txt Download as CSV file: xf-raf31-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 31 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6958 0.07527 0.07108 -0.0589 1.0000 0.0278
-13.000 -0.7411 0.06368 0.05926 -0.0676 1.0000 0.0273
-12.750 -0.7694 0.05648 0.05184 -0.0727 1.0000 0.0273
-12.500 -0.7914 0.05122 0.04638 -0.0756 1.0000 0.0275
-12.250 -0.8100 0.04719 0.04215 -0.0766 1.0000 0.0276
-12.000 -0.8255 0.04422 0.03900 -0.0760 1.0000 0.0278
-11.750 -0.8408 0.04192 0.03651 -0.0736 1.0000 0.0281
-11.500 -0.8555 0.04018 0.03461 -0.0695 1.0000 0.0284
-11.250 -0.8633 0.03849 0.03271 -0.0660 1.0000 0.0288
-11.000 -0.8667 0.03693 0.03093 -0.0627 1.0000 0.0292
-10.750 -0.8673 0.03561 0.02938 -0.0594 1.0000 0.0296
-10.500 -0.8678 0.03371 0.02732 -0.0562 1.0000 0.0301
-10.250 -0.8650 0.03219 0.02571 -0.0531 1.0000 0.0306
-10.000 -0.8475 0.03071 0.02413 -0.0528 0.9977 0.0312
-9.750 -0.8204 0.02928 0.02258 -0.0542 0.9933 0.0321
-9.500 -0.7939 0.02799 0.02114 -0.0552 0.9881 0.0331
-9.250 -0.7658 0.02670 0.01968 -0.0565 0.9837 0.0341
-9.000 -0.7403 0.02546 0.01826 -0.0569 0.9775 0.0348
-8.750 -0.7110 0.02430 0.01693 -0.0580 0.9733 0.0355
-8.500 -0.6858 0.02336 0.01584 -0.0582 0.9663 0.0363
-8.250 -0.6560 0.02244 0.01478 -0.0592 0.9620 0.0370
-8.000 -0.6318 0.02122 0.01352 -0.0592 0.9554 0.0379
-7.750 -0.6032 0.02026 0.01250 -0.0600 0.9505 0.0387
-7.500 -0.5735 0.01942 0.01160 -0.0609 0.9461 0.0395
-7.250 -0.5456 0.01870 0.01082 -0.0614 0.9402 0.0404
-7.000 -0.5136 0.01800 0.01005 -0.0627 0.9362 0.0415
-6.750 -0.4815 0.01737 0.00933 -0.0640 0.9321 0.0428
-6.500 -0.4526 0.01682 0.00870 -0.0645 0.9258 0.0443
-6.250 -0.4202 0.01623 0.00805 -0.0657 0.9214 0.0459
-6.000 -0.3883 0.01569 0.00746 -0.0669 0.9168 0.0481
-5.750 -0.3593 0.01526 0.00700 -0.0673 0.9100 0.0508
-5.500 -0.3258 0.01481 0.00653 -0.0687 0.9048 0.0558
-5.250 -0.2979 0.01445 0.00616 -0.0688 0.8968 0.0657
-5.000 -0.2672 0.01409 0.00579 -0.0695 0.8903 0.0796
-4.750 -0.2408 0.01379 0.00548 -0.0693 0.8824 0.0931
-4.500 -0.2135 0.01343 0.00515 -0.0693 0.8755 0.1095
-4.250 -0.1889 0.01307 0.00488 -0.0688 0.8676 0.1334
-4.000 -0.1633 0.01269 0.00463 -0.0685 0.8600 0.1684
-3.750 -0.1390 0.01241 0.00442 -0.0679 0.8521 0.2029
-3.500 -0.1138 0.01209 0.00422 -0.0675 0.8448 0.2408
-3.250 -0.0902 0.01180 0.00408 -0.0667 0.8371 0.2864
-3.000 -0.0650 0.01158 0.00395 -0.0662 0.8300 0.3241
-2.750 -0.0401 0.01140 0.00386 -0.0656 0.8226 0.3585
-2.500 -0.0155 0.01119 0.00376 -0.0649 0.8151 0.4004
-2.250 0.0085 0.01098 0.00369 -0.0641 0.8075 0.4408
-2.000 0.0331 0.01080 0.00362 -0.0633 0.7992 0.4790
-1.750 0.0576 0.01066 0.00355 -0.0625 0.7899 0.5084
-1.500 0.0837 0.01054 0.00346 -0.0619 0.7815 0.5360
-1.250 0.1085 0.01045 0.00341 -0.0611 0.7716 0.5609
-1.000 0.1345 0.01037 0.00336 -0.0605 0.7641 0.5885
-0.750 0.1593 0.01029 0.00335 -0.0597 0.7559 0.6163
-0.500 0.1853 0.01021 0.00333 -0.0591 0.7494 0.6449
-0.250 0.2099 0.01016 0.00336 -0.0582 0.7415 0.6732
0.000 0.2355 0.01010 0.00336 -0.0575 0.7345 0.7053
0.250 0.2601 0.01006 0.00341 -0.0566 0.7262 0.7329
0.500 0.2864 0.01003 0.00340 -0.0560 0.7186 0.7568
0.750 0.3118 0.01001 0.00344 -0.0552 0.7095 0.7781
1.000 0.3386 0.01000 0.00345 -0.0548 0.7014 0.7997
1.250 0.3655 0.00999 0.00349 -0.0543 0.6919 0.8216
1.500 0.3947 0.00999 0.00354 -0.0544 0.6830 0.8444
1.750 0.4271 0.01001 0.00360 -0.0552 0.6738 0.8679
2.000 0.4643 0.01006 0.00369 -0.0570 0.6644 0.8917
2.250 0.5056 0.01013 0.00378 -0.0597 0.6546 0.9135
2.500 0.5478 0.01020 0.00389 -0.0627 0.6428 0.9329
2.750 0.5875 0.01029 0.00398 -0.0651 0.6292 0.9522
3.000 0.6240 0.01040 0.00405 -0.0669 0.6109 0.9702
3.250 0.6585 0.01054 0.00412 -0.0684 0.5862 0.9864
3.500 0.6931 0.01072 0.00420 -0.0699 0.5553 1.0000
3.750 0.7103 0.01092 0.00426 -0.0677 0.5260 1.0000
4.000 0.7270 0.01118 0.00436 -0.0655 0.4962 1.0000
4.250 0.7442 0.01148 0.00452 -0.0634 0.4717 1.0000
4.500 0.7618 0.01180 0.00472 -0.0614 0.4504 1.0000
4.750 0.7799 0.01212 0.00494 -0.0595 0.4301 1.0000
5.000 0.7980 0.01244 0.00519 -0.0576 0.4100 1.0000
5.250 0.8160 0.01278 0.00546 -0.0557 0.3885 1.0000
5.500 0.8350 0.01306 0.00571 -0.0540 0.3624 1.0000
5.750 0.8515 0.01345 0.00598 -0.0519 0.3221 1.0000
6.000 0.8629 0.01407 0.00632 -0.0489 0.2788 1.0000
6.250 0.8764 0.01466 0.00678 -0.0464 0.2546 1.0000
6.500 0.8924 0.01516 0.00722 -0.0444 0.2275 1.0000
6.750 0.9049 0.01584 0.00768 -0.0418 0.1794 1.0000
7.000 0.9159 0.01660 0.00822 -0.0390 0.1481 1.0000
7.250 0.9295 0.01723 0.00878 -0.0367 0.1318 1.0000
7.500 0.9430 0.01784 0.00936 -0.0343 0.1216 1.0000
7.750 0.9569 0.01836 0.00989 -0.0319 0.1136 1.0000
8.000 0.9685 0.01898 0.01048 -0.0293 0.1068 1.0000
8.250 0.9829 0.01949 0.01103 -0.0271 0.1004 1.0000
8.500 0.9942 0.02017 0.01168 -0.0246 0.0941 1.0000
8.750 1.0096 0.02068 0.01226 -0.0227 0.0886 1.0000
9.000 1.0231 0.02129 0.01290 -0.0207 0.0835 1.0000
9.250 1.0352 0.02201 0.01362 -0.0186 0.0795 1.0000
9.500 1.0508 0.02256 0.01426 -0.0170 0.0748 1.0000
9.750 1.0638 0.02326 0.01497 -0.0152 0.0698 1.0000
10.000 1.0772 0.02398 0.01575 -0.0134 0.0657 1.0000
10.250 1.0915 0.02466 0.01650 -0.0119 0.0608 1.0000
10.500 1.1028 0.02554 0.01738 -0.0102 0.0562 1.0000
10.750 1.1173 0.02627 0.01821 -0.0088 0.0504 1.0000
11.000 1.1287 0.02721 0.01917 -0.0072 0.0448 1.0000
11.250 1.1394 0.02824 0.02021 -0.0056 0.0378 1.0000
11.750 1.1562 0.03074 0.02274 -0.0024 0.0271 1.0000
12.000 1.1627 0.03221 0.02424 -0.0008 0.0248 1.0000
12.250 1.1689 0.03374 0.02584 0.0006 0.0227 1.0000
12.500 1.1742 0.03538 0.02755 0.0020 0.0216 1.0000
12.750 1.1769 0.03731 0.02953 0.0033 0.0206 1.0000
13.000 1.1810 0.03918 0.03153 0.0045 0.0198 1.0000
13.250 1.1843 0.04117 0.03365 0.0054 0.0192 1.0000
13.500 1.1867 0.04332 0.03593 0.0063 0.0186 1.0000
13.750 1.1879 0.04564 0.03837 0.0070 0.0180 1.0000
14.000 1.1880 0.04814 0.04099 0.0075 0.0175 1.0000
14.250 1.1867 0.05089 0.04384 0.0078 0.0170 1.0000
14.500 1.1823 0.05407 0.04711 0.0079 0.0164 1.0000
14.750 1.1766 0.05754 0.05068 0.0078 0.0161 1.0000
15.000 1.1752 0.06066 0.05395 0.0075 0.0159 1.0000
15.250 1.1734 0.06393 0.05736 0.0070 0.0157 1.0000
15.500 1.1698 0.06758 0.06117 0.0063 0.0153 1.0000
15.750 1.1655 0.07142 0.06514 0.0054 0.0151 1.0000
16.000 1.1603 0.07553 0.06941 0.0042 0.0148 1.0000
16.250 1.1543 0.07989 0.07390 0.0028 0.0147 1.0000
16.500 1.1477 0.08448 0.07865 0.0011 0.0145 1.0000
16.750 1.1399 0.08936 0.08368 -0.0008 0.0143 1.0000
17.000 1.1317 0.09443 0.08889 -0.0029 0.0141 1.0000
17.250 1.1231 0.09970 0.09430 -0.0052 0.0140 1.0000
17.500 1.1135 0.10530 0.10004 -0.0078 0.0139 1.0000
17.750 1.1034 0.11111 0.10600 -0.0106 0.0138 1.0000
18.000 1.0919 0.11737 0.11239 -0.0138 0.0137 1.0000
18.250 1.0808 0.12378 0.11895 -0.0172 0.0137 1.0000
18.500 1.0682 0.13071 0.12602 -0.0211 0.0136 1.0000
18.750 1.0544 0.13807 0.13353 -0.0252 0.0135 1.0000
19.000 1.0385 0.14622 0.14184 -0.0300 0.0136 1.0000
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