RAF 38 AIRFOIL (raf38-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 38 AIRFOIL (raf38-il) Reynolds number: 200,000 Max Cl/Cd: 71.46 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf38-il-200000.txt Download as CSV file: xf-raf38-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6022 0.06532 0.06137 -0.0644 1.0000 0.0506
-10.500 -0.6173 0.06084 0.05687 -0.0647 1.0000 0.0502
-10.250 -0.6404 0.05724 0.05320 -0.0628 1.0000 0.0498
-10.000 -0.6640 0.05379 0.04965 -0.0596 1.0000 0.0495
-9.750 -0.6832 0.05009 0.04577 -0.0565 1.0000 0.0492
-9.500 -0.7005 0.04641 0.04185 -0.0529 1.0000 0.0490
-9.250 -0.7144 0.04303 0.03819 -0.0488 1.0000 0.0491
-9.000 -0.7259 0.04014 0.03500 -0.0442 1.0000 0.0494
-8.750 -0.7377 0.03805 0.03262 -0.0390 1.0000 0.0498
-8.500 -0.7422 0.03670 0.03086 -0.0349 0.9984 0.0507
-8.250 -0.7131 0.03300 0.02704 -0.0377 0.9929 0.0531
-8.000 -0.6785 0.03133 0.02526 -0.0402 0.9865 0.0555
-7.750 -0.6460 0.02905 0.02254 -0.0422 0.9798 0.0581
-7.500 -0.6139 0.02694 0.01991 -0.0439 0.9726 0.0611
-7.250 -0.5794 0.02504 0.01799 -0.0461 0.9670 0.0643
-7.000 -0.5442 0.02380 0.01659 -0.0480 0.9602 0.0676
-6.750 -0.5037 0.02301 0.01545 -0.0505 0.9562 0.0713
-6.500 -0.4714 0.02089 0.01333 -0.0520 0.9487 0.0751
-6.250 -0.4330 0.01997 0.01234 -0.0543 0.9434 0.0796
-6.000 -0.3961 0.01921 0.01139 -0.0561 0.9373 0.0831
-5.750 -0.3629 0.01787 0.01007 -0.0574 0.9294 0.0874
-5.500 -0.3265 0.01708 0.00927 -0.0591 0.9233 0.0918
-5.250 -0.2965 0.01654 0.00863 -0.0594 0.9132 0.0959
-5.000 -0.2668 0.01568 0.00781 -0.0598 0.9050 0.1002
-4.750 -0.2390 0.01517 0.00730 -0.0598 0.8953 0.1055
-4.500 -0.2127 0.01478 0.00683 -0.0593 0.8853 0.1110
-4.250 -0.1866 0.01421 0.00630 -0.0588 0.8760 0.1185
-4.000 -0.1642 0.01382 0.00593 -0.0575 0.8640 0.1293
-3.750 -0.1411 0.01337 0.00560 -0.0565 0.8540 0.1552
-3.500 -0.1199 0.01270 0.00527 -0.0552 0.8451 0.2338
-3.250 -0.1002 0.01218 0.00510 -0.0538 0.8360 0.3110
-3.000 -0.0790 0.01174 0.00497 -0.0525 0.8283 0.4013
-2.750 -0.0589 0.01144 0.00494 -0.0509 0.8197 0.4805
-2.500 -0.0370 0.01115 0.00487 -0.0494 0.8124 0.5511
-2.250 -0.0163 0.01093 0.00490 -0.0477 0.8044 0.6199
-2.000 0.0063 0.01074 0.00493 -0.0461 0.7972 0.6916
-1.750 0.0303 0.01065 0.00501 -0.0447 0.7901 0.7547
-1.500 0.0573 0.01061 0.00508 -0.0438 0.7825 0.8096
-1.250 0.0919 0.01067 0.00517 -0.0443 0.7765 0.8538
-1.000 0.1294 0.01081 0.00533 -0.0456 0.7687 0.8882
-0.750 0.1744 0.01103 0.00544 -0.0483 0.7625 0.9139
-0.500 0.2183 0.01125 0.00561 -0.0510 0.7545 0.9314
-0.250 0.2624 0.01140 0.00566 -0.0539 0.7475 0.9434
0.000 0.3061 0.01157 0.00576 -0.0569 0.7398 0.9561
0.250 0.3567 0.01168 0.00578 -0.0612 0.7318 0.9676
0.500 0.4087 0.01175 0.00579 -0.0661 0.7235 0.9787
0.750 0.4606 0.01172 0.00569 -0.0710 0.7152 0.9893
1.000 0.5091 0.01161 0.00554 -0.0755 0.7059 0.9984
1.250 0.5353 0.01155 0.00542 -0.0754 0.6976 1.0000
1.500 0.5544 0.01156 0.00542 -0.0740 0.6881 1.0000
1.750 0.5757 0.01155 0.00533 -0.0728 0.6801 1.0000
2.000 0.5948 0.01155 0.00533 -0.0712 0.6690 1.0000
2.250 0.6150 0.01154 0.00529 -0.0698 0.6579 1.0000
2.500 0.6363 0.01152 0.00518 -0.0684 0.6470 1.0000
2.750 0.6564 0.01153 0.00519 -0.0669 0.6349 1.0000
3.000 0.6773 0.01161 0.00526 -0.0655 0.6245 1.0000
3.250 0.6997 0.01167 0.00526 -0.0644 0.6153 1.0000
3.500 0.7202 0.01174 0.00535 -0.0629 0.6032 1.0000
3.750 0.7412 0.01181 0.00542 -0.0615 0.5910 1.0000
4.000 0.7624 0.01188 0.00546 -0.0601 0.5787 1.0000
4.250 0.7837 0.01196 0.00549 -0.0587 0.5658 1.0000
4.500 0.8049 0.01205 0.00556 -0.0572 0.5528 1.0000
4.750 0.8257 0.01217 0.00572 -0.0558 0.5397 1.0000
5.000 0.8466 0.01229 0.00584 -0.0543 0.5260 1.0000
5.250 0.8672 0.01243 0.00597 -0.0528 0.5114 1.0000
5.500 0.8876 0.01259 0.00613 -0.0513 0.4964 1.0000
5.750 0.9075 0.01277 0.00628 -0.0497 0.4799 1.0000
6.000 0.9271 0.01299 0.00647 -0.0480 0.4631 1.0000
6.250 0.9461 0.01324 0.00669 -0.0463 0.4456 1.0000
6.500 0.9648 0.01353 0.00695 -0.0445 0.4279 1.0000
6.750 0.9829 0.01382 0.00723 -0.0426 0.4083 1.0000
7.000 1.0001 0.01413 0.00754 -0.0406 0.3861 1.0000
7.250 1.0158 0.01448 0.00786 -0.0384 0.3599 1.0000
7.500 1.0294 0.01491 0.00821 -0.0358 0.3249 1.0000
7.750 1.0376 0.01559 0.00866 -0.0325 0.2771 1.0000
8.000 1.0400 0.01662 0.00936 -0.0283 0.2239 1.0000
8.250 1.0386 0.01789 0.01026 -0.0238 0.1679 1.0000
8.500 1.0386 0.01910 0.01119 -0.0195 0.1303 1.0000
8.750 1.0389 0.02011 0.01207 -0.0152 0.1147 1.0000
9.000 1.0425 0.02104 0.01296 -0.0115 0.1053 1.0000
9.250 1.0444 0.02214 0.01401 -0.0080 0.0983 1.0000
9.500 1.0512 0.02312 0.01503 -0.0053 0.0923 1.0000
9.750 1.0516 0.02456 0.01640 -0.0022 0.0872 1.0000
10.000 1.0611 0.02557 0.01750 -0.0002 0.0827 1.0000
10.250 1.0675 0.02684 0.01878 0.0019 0.0781 1.0000
10.500 1.0726 0.02843 0.02033 0.0040 0.0741 1.0000
10.750 1.0828 0.02959 0.02159 0.0056 0.0702 1.0000
11.000 1.0915 0.03095 0.02294 0.0071 0.0664 1.0000
11.250 1.1037 0.03251 0.02446 0.0086 0.0629 1.0000
11.500 1.1142 0.03376 0.02585 0.0099 0.0598 1.0000
11.750 1.1250 0.03507 0.02718 0.0111 0.0568 1.0000
12.000 1.1450 0.03672 0.02873 0.0120 0.0536 1.0000
12.250 1.1538 0.03809 0.03029 0.0133 0.0517 1.0000
12.500 1.1632 0.03954 0.03187 0.0144 0.0495 1.0000
12.750 1.1731 0.04100 0.03337 0.0154 0.0475 1.0000
13.000 1.1953 0.04281 0.03510 0.0159 0.0450 1.0000
13.250 1.1992 0.04461 0.03713 0.0172 0.0439 1.0000
13.500 1.2053 0.04656 0.03929 0.0183 0.0427 1.0000
13.750 1.2104 0.04854 0.04142 0.0192 0.0413 1.0000
14.000 1.2150 0.05054 0.04354 0.0200 0.0402 1.0000
14.250 1.2219 0.05237 0.04540 0.0206 0.0390 1.0000
14.500 1.2365 0.05500 0.04805 0.0211 0.0377 1.0000
14.750 1.2255 0.05785 0.05118 0.0218 0.0371 1.0000
15.000 1.2186 0.06122 0.05480 0.0222 0.0367 1.0000
15.250 1.2073 0.06495 0.05879 0.0222 0.0362 1.0000
15.500 1.1962 0.06906 0.06315 0.0219 0.0360 1.0000
15.750 1.1817 0.07355 0.06787 0.0211 0.0356 1.0000
16.000 1.1649 0.07861 0.07317 0.0199 0.0355 1.0000
16.250 1.1449 0.08434 0.07913 0.0179 0.0353 1.0000
16.500 1.1225 0.09080 0.08582 0.0152 0.0353 1.0000
16.750 1.0958 0.09847 0.09373 0.0115 0.0354 1.0000
17.000 1.0657 0.10730 0.10278 0.0067 0.0356 1.0000
17.250 1.0312 0.11774 0.11344 0.0005 0.0361 1.0000
17.500 0.9915 0.13034 0.12622 -0.0072 0.0367 1.0000
17.750 0.9526 0.14407 0.14007 -0.0156 0.0374 1.0000
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