RAF 38 AIRFOIL (raf38-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 38 AIRFOIL (raf38-il) Reynolds number: 100,000 Max Cl/Cd: 51.87 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf38-il-100000-n5.txt Download as CSV file: xf-raf38-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4967 0.09051 0.08525 -0.0431 1.0000 0.0395
-11.000 -0.5253 0.07989 0.07471 -0.0490 1.0000 0.0396
-10.750 -0.5878 0.06288 0.05768 -0.0621 1.0000 0.0381
-10.500 -0.6324 0.05558 0.05022 -0.0656 1.0000 0.0373
-10.250 -0.6648 0.05178 0.04627 -0.0630 1.0000 0.0372
-10.000 -0.6862 0.04842 0.04270 -0.0600 1.0000 0.0376
-9.750 -0.7010 0.04532 0.03933 -0.0567 1.0000 0.0384
-9.500 -0.7116 0.04233 0.03602 -0.0533 1.0000 0.0395
-9.250 -0.7204 0.03942 0.03265 -0.0495 1.0000 0.0410
-9.000 -0.7224 0.03723 0.03016 -0.0461 1.0000 0.0422
-8.750 -0.7167 0.03618 0.02911 -0.0433 1.0000 0.0434
-8.500 -0.7023 0.03496 0.02778 -0.0423 0.9968 0.0453
-8.250 -0.6734 0.03302 0.02545 -0.0441 0.9875 0.0491
-8.000 -0.6454 0.03081 0.02263 -0.0454 0.9780 0.0528
-7.750 -0.6150 0.02948 0.02133 -0.0470 0.9695 0.0562
-7.500 -0.5839 0.02815 0.01972 -0.0484 0.9612 0.0607
-7.250 -0.5520 0.02669 0.01792 -0.0498 0.9535 0.0652
-7.000 -0.5215 0.02559 0.01682 -0.0510 0.9448 0.0693
-6.750 -0.4885 0.02460 0.01559 -0.0524 0.9374 0.0745
-6.500 -0.4573 0.02350 0.01435 -0.0534 0.9289 0.0787
-6.250 -0.4269 0.02265 0.01347 -0.0543 0.9202 0.0833
-6.000 -0.3941 0.02184 0.01252 -0.0554 0.9129 0.0879
-5.750 -0.3655 0.02105 0.01164 -0.0558 0.9035 0.0921
-5.500 -0.3338 0.02030 0.01087 -0.0567 0.8964 0.0963
-5.250 -0.3069 0.01973 0.01023 -0.0566 0.8866 0.1006
-5.000 -0.2763 0.01912 0.00955 -0.0572 0.8797 0.1067
-4.750 -0.2509 0.01864 0.00906 -0.0568 0.8699 0.1131
-4.500 -0.2213 0.01812 0.00849 -0.0571 0.8631 0.1215
-4.250 -0.1970 0.01771 0.00808 -0.0565 0.8534 0.1336
-4.000 -0.1691 0.01721 0.00767 -0.0566 0.8466 0.1575
-3.750 -0.1454 0.01683 0.00739 -0.0559 0.8370 0.1940
-3.500 -0.1187 0.01638 0.00705 -0.0557 0.8298 0.2384
-3.250 -0.0957 0.01600 0.00683 -0.0548 0.8198 0.2839
-3.000 -0.0709 0.01560 0.00661 -0.0542 0.8114 0.3408
-2.750 -0.0475 0.01528 0.00648 -0.0532 0.8020 0.4040
-2.500 -0.0240 0.01496 0.00638 -0.0522 0.7939 0.4776
-2.250 -0.0008 0.01465 0.00633 -0.0510 0.7857 0.5518
-2.000 0.0240 0.01436 0.00635 -0.0498 0.7787 0.6397
-1.750 0.0505 0.01421 0.00645 -0.0489 0.7709 0.7211
-1.500 0.0838 0.01414 0.00647 -0.0490 0.7650 0.7864
-1.250 0.1175 0.01419 0.00654 -0.0497 0.7567 0.8288
-1.000 0.1564 0.01424 0.00651 -0.0513 0.7505 0.8599
-0.750 0.1955 0.01434 0.00656 -0.0532 0.7426 0.8852
-0.500 0.2346 0.01444 0.00656 -0.0550 0.7356 0.9110
-0.250 0.2790 0.01458 0.00662 -0.0580 0.7281 0.9360
0.000 0.3264 0.01468 0.00664 -0.0616 0.7205 0.9563
0.250 0.3705 0.01473 0.00661 -0.0649 0.7131 0.9721
0.500 0.4117 0.01475 0.00656 -0.0678 0.7048 0.9842
0.750 0.4532 0.01472 0.00647 -0.0708 0.6968 0.9941
1.000 0.4866 0.01472 0.00642 -0.0723 0.6883 1.0000
1.250 0.5068 0.01477 0.00643 -0.0710 0.6804 1.0000
1.500 0.5270 0.01485 0.00647 -0.0697 0.6718 1.0000
1.750 0.5477 0.01494 0.00652 -0.0684 0.6634 1.0000
2.000 0.5686 0.01503 0.00660 -0.0671 0.6549 1.0000
2.250 0.5895 0.01515 0.00670 -0.0658 0.6463 1.0000
2.500 0.6110 0.01525 0.00678 -0.0646 0.6377 1.0000
2.750 0.6318 0.01540 0.00694 -0.0633 0.6283 1.0000
3.000 0.6543 0.01550 0.00700 -0.0622 0.6198 1.0000
3.250 0.6744 0.01564 0.00717 -0.0607 0.6080 1.0000
3.500 0.6954 0.01575 0.00726 -0.0593 0.5961 1.0000
3.750 0.7172 0.01584 0.00733 -0.0580 0.5847 1.0000
4.000 0.7381 0.01599 0.00750 -0.0566 0.5730 1.0000
4.250 0.7591 0.01618 0.00772 -0.0553 0.5620 1.0000
4.500 0.7812 0.01634 0.00789 -0.0541 0.5522 1.0000
4.750 0.8025 0.01654 0.00812 -0.0528 0.5412 1.0000
5.000 0.8233 0.01674 0.00838 -0.0514 0.5293 1.0000
5.250 0.8441 0.01693 0.00859 -0.0500 0.5166 1.0000
5.500 0.8645 0.01712 0.00879 -0.0485 0.5024 1.0000
5.750 0.8842 0.01732 0.00899 -0.0469 0.4867 1.0000
6.000 0.9033 0.01756 0.00922 -0.0451 0.4697 1.0000
6.250 0.9222 0.01783 0.00950 -0.0434 0.4531 1.0000
6.500 0.9404 0.01813 0.00980 -0.0416 0.4353 1.0000
6.750 0.9575 0.01848 0.01011 -0.0396 0.4153 1.0000
7.000 0.9738 0.01886 0.01048 -0.0376 0.3946 1.0000
7.250 0.9899 0.01928 0.01093 -0.0356 0.3739 1.0000
7.500 1.0058 0.01971 0.01139 -0.0335 0.3535 1.0000
7.750 1.0204 0.02020 0.01188 -0.0313 0.3317 1.0000
8.000 1.0337 0.02074 0.01243 -0.0290 0.3064 1.0000
8.250 1.0442 0.02140 0.01302 -0.0263 0.2792 1.0000
8.500 1.0515 0.02222 0.01371 -0.0232 0.2506 1.0000
8.750 1.0558 0.02317 0.01453 -0.0199 0.2231 1.0000
9.000 1.0574 0.02420 0.01544 -0.0161 0.1965 1.0000
9.250 1.0590 0.02533 0.01647 -0.0127 0.1702 1.0000
9.500 1.0592 0.02664 0.01767 -0.0095 0.1472 1.0000
9.750 1.0605 0.02804 0.01897 -0.0067 0.1285 1.0000
10.000 1.0617 0.02954 0.02040 -0.0042 0.1156 1.0000
10.250 1.0642 0.03108 0.02191 -0.0021 0.1056 1.0000
10.500 1.0674 0.03265 0.02351 -0.0002 0.0980 1.0000
10.750 1.0693 0.03441 0.02527 0.0015 0.0915 1.0000
11.000 1.0729 0.03613 0.02704 0.0030 0.0857 1.0000
11.250 1.0758 0.03797 0.02893 0.0043 0.0803 1.0000
11.500 1.0776 0.03997 0.03096 0.0055 0.0759 1.0000
11.750 1.0822 0.04181 0.03293 0.0065 0.0707 1.0000
12.000 1.0827 0.04404 0.03516 0.0075 0.0667 1.0000
12.250 1.0873 0.04601 0.03726 0.0083 0.0624 1.0000
12.500 1.0899 0.04820 0.03952 0.0090 0.0583 1.0000
12.750 1.0908 0.05056 0.04186 0.0097 0.0554 1.0000
13.000 1.0963 0.05265 0.04415 0.0103 0.0518 1.0000
13.250 1.0992 0.05498 0.04659 0.0107 0.0486 1.0000
13.500 1.1001 0.05752 0.04920 0.0109 0.0461 1.0000
13.750 1.1033 0.05995 0.05171 0.0113 0.0440 1.0000
14.000 1.1068 0.06247 0.05443 0.0115 0.0415 1.0000
14.250 1.1080 0.06523 0.05734 0.0114 0.0393 1.0000
14.500 1.1079 0.06822 0.06042 0.0111 0.0375 1.0000
14.750 1.1084 0.07117 0.06344 0.0108 0.0363 1.0000
15.000 1.1087 0.07420 0.06650 0.0105 0.0351 1.0000
15.250 1.1071 0.07778 0.07034 0.0099 0.0338 1.0000
15.500 1.1048 0.08152 0.07428 0.0091 0.0328 1.0000
15.750 1.1003 0.08564 0.07860 0.0080 0.0317 1.0000
16.000 1.0946 0.09002 0.08314 0.0064 0.0308 1.0000
16.250 1.0885 0.09457 0.08785 0.0047 0.0301 1.0000
16.500 1.0814 0.09942 0.09285 0.0028 0.0295 1.0000
16.750 1.0734 0.10453 0.09809 0.0005 0.0290 1.0000
17.000 1.0646 0.10994 0.10367 -0.0020 0.0286 1.0000
17.250 1.0548 0.11567 0.10953 -0.0048 0.0282 1.0000
17.500 1.0440 0.12178 0.11577 -0.0080 0.0279 1.0000
17.750 1.0261 0.12973 0.12391 -0.0125 0.0278 1.0000
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