RAF 38 AIRFOIL (raf38-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 38 AIRFOIL (raf38-il) Reynolds number: 200,000 Max Cl/Cd: 69.04 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf38-il-200000-n5.txt Download as CSV file: xf-raf38-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 38 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 -0.7303 0.06770 0.06367 -0.0561 1.0000 0.0198
-13.000 -0.7804 0.05426 0.04995 -0.0669 1.0000 0.0194
-12.750 -0.8063 0.04745 0.04290 -0.0718 1.0000 0.0193
-12.500 -0.8248 0.04308 0.03832 -0.0734 1.0000 0.0194
-12.250 -0.8401 0.03988 0.03493 -0.0727 1.0000 0.0196
-12.000 -0.8523 0.03749 0.03234 -0.0703 1.0000 0.0198
-11.750 -0.8627 0.03558 0.03025 -0.0666 1.0000 0.0201
-11.500 -0.8683 0.03374 0.02819 -0.0631 1.0000 0.0206
-11.250 -0.8682 0.03203 0.02624 -0.0601 1.0000 0.0211
-11.000 -0.8642 0.03073 0.02488 -0.0574 1.0000 0.0216
-10.750 -0.8554 0.02988 0.02396 -0.0551 1.0000 0.0224
-10.500 -0.8461 0.02896 0.02296 -0.0527 1.0000 0.0232
-10.250 -0.8371 0.02793 0.02180 -0.0502 1.0000 0.0241
-10.000 -0.8284 0.02681 0.02051 -0.0476 1.0000 0.0251
-9.750 -0.8159 0.02560 0.01909 -0.0456 0.9990 0.0262
-9.500 -0.7849 0.02465 0.01810 -0.0473 0.9916 0.0277
-9.250 -0.7523 0.02398 0.01733 -0.0490 0.9846 0.0298
-9.000 -0.7220 0.02299 0.01613 -0.0502 0.9761 0.0323
-8.750 -0.6917 0.02217 0.01524 -0.0514 0.9669 0.0344
-8.500 -0.6590 0.02173 0.01473 -0.0528 0.9577 0.0372
-8.250 -0.6267 0.02106 0.01385 -0.0541 0.9482 0.0406
-8.000 -0.5943 0.02033 0.01302 -0.0555 0.9388 0.0436
-7.750 -0.5617 0.01986 0.01248 -0.0568 0.9278 0.0469
-7.500 -0.5293 0.01935 0.01178 -0.0579 0.9160 0.0507
-7.250 -0.4979 0.01865 0.01094 -0.0589 0.9041 0.0537
-7.000 -0.4674 0.01807 0.01032 -0.0598 0.8926 0.0570
-6.750 -0.4377 0.01759 0.00973 -0.0603 0.8807 0.0604
-6.500 -0.4094 0.01720 0.00916 -0.0604 0.8685 0.0632
-6.250 -0.3835 0.01656 0.00847 -0.0602 0.8572 0.0661
-5.750 -0.3327 0.01571 0.00747 -0.0594 0.8368 0.0719
-5.500 -0.3073 0.01537 0.00702 -0.0590 0.8278 0.0746
-5.250 -0.2821 0.01508 0.00662 -0.0584 0.8186 0.0767
-5.000 -0.2585 0.01463 0.00613 -0.0576 0.8104 0.0796
-4.750 -0.2341 0.01431 0.00576 -0.0570 0.8022 0.0824
-4.250 -0.1843 0.01381 0.00511 -0.0557 0.7858 0.0906
-4.000 -0.1601 0.01351 0.00480 -0.0550 0.7765 0.0973
-3.750 -0.1356 0.01325 0.00451 -0.0543 0.7673 0.1080
-3.500 -0.1117 0.01292 0.00429 -0.0536 0.7584 0.1351
-3.250 -0.0872 0.01263 0.00411 -0.0529 0.7514 0.1746
-3.000 -0.0623 0.01241 0.00395 -0.0524 0.7446 0.2053
-2.750 -0.0375 0.01219 0.00379 -0.0518 0.7377 0.2346
-2.500 -0.0130 0.01193 0.00364 -0.0512 0.7317 0.2728
-2.250 0.0101 0.01160 0.00354 -0.0503 0.7246 0.3327
-2.000 0.0329 0.01127 0.00346 -0.0494 0.7185 0.4104
-1.750 0.0561 0.01102 0.00341 -0.0484 0.7121 0.4715
-1.500 0.0796 0.01080 0.00336 -0.0475 0.7054 0.5251
-1.250 0.1027 0.01058 0.00332 -0.0463 0.6996 0.5843
-1.000 0.1257 0.01037 0.00334 -0.0451 0.6926 0.6455
-0.750 0.1498 0.01021 0.00336 -0.0440 0.6867 0.7079
-0.500 0.1758 0.01009 0.00341 -0.0432 0.6805 0.7699
-0.250 0.2062 0.01003 0.00348 -0.0433 0.6735 0.8206
0.000 0.2427 0.01006 0.00352 -0.0447 0.6673 0.8604
0.250 0.2830 0.01013 0.00362 -0.0470 0.6597 0.8905
0.500 0.3241 0.01023 0.00368 -0.0495 0.6531 0.9149
0.750 0.3626 0.01033 0.00376 -0.0515 0.6454 0.9330
1.000 0.4005 0.01043 0.00380 -0.0534 0.6377 0.9484
1.250 0.4384 0.01053 0.00388 -0.0554 0.6301 0.9604
1.500 0.4758 0.01061 0.00392 -0.0574 0.6220 0.9695
1.750 0.5115 0.01068 0.00397 -0.0591 0.6136 0.9773
2.000 0.5467 0.01076 0.00400 -0.0607 0.6049 0.9847
2.250 0.5845 0.01080 0.00403 -0.0629 0.5946 0.9906
2.500 0.6210 0.01084 0.00403 -0.0648 0.5819 0.9966
2.750 0.6519 0.01090 0.00404 -0.0656 0.5677 1.0000
3.000 0.6728 0.01098 0.00407 -0.0643 0.5553 1.0000
3.250 0.6943 0.01107 0.00417 -0.0631 0.5439 1.0000
3.500 0.7155 0.01118 0.00426 -0.0618 0.5317 1.0000
3.750 0.7365 0.01131 0.00435 -0.0605 0.5182 1.0000
4.000 0.7574 0.01146 0.00446 -0.0591 0.5044 1.0000
4.250 0.7782 0.01163 0.00459 -0.0577 0.4909 1.0000
4.500 0.7992 0.01181 0.00475 -0.0564 0.4778 1.0000
4.750 0.8198 0.01202 0.00492 -0.0550 0.4634 1.0000
5.000 0.8400 0.01224 0.00511 -0.0535 0.4485 1.0000
5.250 0.8599 0.01249 0.00533 -0.0520 0.4328 1.0000
5.500 0.8797 0.01276 0.00556 -0.0505 0.4176 1.0000
5.750 0.8996 0.01303 0.00581 -0.0491 0.4031 1.0000
6.000 0.9189 0.01332 0.00608 -0.0475 0.3860 1.0000
6.250 0.9378 0.01362 0.00637 -0.0458 0.3680 1.0000
6.500 0.9556 0.01397 0.00667 -0.0440 0.3471 1.0000
6.750 0.9736 0.01432 0.00700 -0.0423 0.3250 1.0000
7.000 0.9896 0.01474 0.00736 -0.0402 0.3006 1.0000
7.250 1.0040 0.01525 0.00777 -0.0379 0.2733 1.0000
7.500 1.0165 0.01586 0.00826 -0.0354 0.2455 1.0000
7.750 1.0282 0.01652 0.00881 -0.0328 0.2200 1.0000
8.000 1.0387 0.01723 0.00941 -0.0301 0.1946 1.0000
8.250 1.0479 0.01799 0.01005 -0.0272 0.1643 1.0000
8.500 1.0529 0.01892 0.01078 -0.0237 0.1304 1.0000
8.750 1.0560 0.01982 0.01153 -0.0200 0.1074 1.0000
9.000 1.0619 0.02066 0.01231 -0.0168 0.0950 1.0000
9.250 1.0691 0.02151 0.01315 -0.0140 0.0868 1.0000
9.500 1.0772 0.02237 0.01402 -0.0115 0.0806 1.0000
9.750 1.0852 0.02330 0.01498 -0.0091 0.0757 1.0000
10.000 1.0946 0.02420 0.01594 -0.0071 0.0712 1.0000
10.250 1.1009 0.02535 0.01711 -0.0050 0.0670 1.0000
10.500 1.1103 0.02637 0.01821 -0.0033 0.0633 1.0000
10.750 1.1189 0.02750 0.01943 -0.0018 0.0593 1.0000
11.000 1.1235 0.02896 0.02091 -0.0001 0.0558 1.0000
11.250 1.1340 0.03007 0.02213 0.0011 0.0520 1.0000
11.500 1.1423 0.03138 0.02352 0.0023 0.0478 1.0000
11.750 1.1475 0.03299 0.02515 0.0035 0.0445 1.0000
12.000 1.1564 0.03436 0.02663 0.0044 0.0402 1.0000
12.250 1.1624 0.03601 0.02832 0.0054 0.0368 1.0000
12.500 1.1661 0.03792 0.03028 0.0063 0.0343 1.0000
12.750 1.1716 0.03971 0.03217 0.0070 0.0318 1.0000
13.000 1.1755 0.04170 0.03422 0.0076 0.0298 1.0000
13.250 1.1766 0.04402 0.03658 0.0082 0.0283 1.0000
13.500 1.1769 0.04647 0.03911 0.0087 0.0269 1.0000
13.750 1.1784 0.04886 0.04162 0.0090 0.0258 1.0000
14.000 1.1798 0.05136 0.04421 0.0092 0.0246 1.0000
14.250 1.1805 0.05398 0.04692 0.0093 0.0235 1.0000
14.500 1.1780 0.05707 0.05007 0.0091 0.0225 1.0000
14.750 1.1749 0.06032 0.05340 0.0089 0.0220 1.0000
15.000 1.1750 0.06327 0.05647 0.0086 0.0213 1.0000
15.250 1.1742 0.06643 0.05976 0.0081 0.0206 1.0000
15.500 1.1735 0.06967 0.06314 0.0075 0.0199 1.0000
15.750 1.1712 0.07318 0.06675 0.0068 0.0194 1.0000
16.000 1.1687 0.07681 0.07049 0.0058 0.0189 1.0000
16.250 1.1657 0.08059 0.07437 0.0047 0.0185 1.0000
16.500 1.1614 0.08464 0.07850 0.0035 0.0181 1.0000
16.750 1.1559 0.08887 0.08279 0.0021 0.0177 1.0000
17.000 1.1526 0.09290 0.08696 0.0008 0.0174 1.0000
17.250 1.1483 0.09723 0.09145 -0.0008 0.0170 1.0000
17.500 1.1436 0.10167 0.09604 -0.0025 0.0167 1.0000
17.750 1.1378 0.10646 0.10097 -0.0046 0.0162 1.0000
18.000 1.1317 0.11131 0.10595 -0.0067 0.0159 1.0000
18.250 1.1252 0.11627 0.11105 -0.0089 0.0158 1.0000
18.500 1.1185 0.12152 0.11641 -0.0116 0.0154 1.0000
18.750 1.1112 0.12691 0.12192 -0.0143 0.0152 1.0000
19.000 1.1038 0.13240 0.12752 -0.0172 0.0150 1.0000
19.250 1.0964 0.13797 0.13319 -0.0202 0.0148 1.0000
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