RAF 33 AIRFOIL (raf33-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 33 AIRFOIL (raf33-il) Reynolds number: 500,000 Max Cl/Cd: 107.71 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf33-il-500000.txt Download as CSV file: xf-raf33-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 33 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2725 0.09098 0.08757 -0.0368 0.6865 0.0332
-9.250 -0.2723 0.08771 0.08429 -0.0383 0.6820 0.0342
-9.000 -0.3028 0.08132 0.07797 -0.0456 0.6784 0.0356
-8.750 -0.2631 0.07063 0.06743 -0.0379 0.6620 0.0362
-8.500 -0.3382 0.07227 0.06889 -0.0477 0.6700 0.0359
-8.250 -0.3357 0.06979 0.06637 -0.0464 0.6657 0.0362
-8.000 -0.3319 0.06733 0.06390 -0.0459 0.6613 0.0364
-7.750 -0.3240 0.06550 0.06205 -0.0452 0.6569 0.0368
-7.500 -0.3186 0.06316 0.05964 -0.0448 0.6529 0.0372
-7.250 -0.3127 0.06072 0.05714 -0.0444 0.6489 0.0377
-7.000 -0.3056 0.05814 0.05451 -0.0441 0.6449 0.0386
-6.750 -0.2997 0.05472 0.05099 -0.0440 0.6411 0.0406
-6.500 -0.3126 0.04553 0.04134 -0.0428 0.6389 0.0428
-6.250 -0.2982 0.04394 0.03969 -0.0418 0.6351 0.0432
-6.000 -0.2825 0.04249 0.03818 -0.0408 0.6314 0.0437
-5.750 -0.2664 0.04084 0.03648 -0.0398 0.6275 0.0443
-5.500 -0.2501 0.03905 0.03458 -0.0388 0.6235 0.0454
-5.250 -0.2361 0.03648 0.03135 -0.0355 0.6204 0.0498
-5.000 -0.2275 0.01805 0.01317 -0.0319 0.6128 0.0511
-4.750 -0.2295 0.02424 0.01800 -0.0280 0.6150 0.0426
-4.500 -0.2079 0.02218 0.01587 -0.0270 0.6113 0.0410
-4.250 -0.1871 0.02029 0.01367 -0.0255 0.6076 0.0408
-4.000 -0.1638 0.01895 0.01206 -0.0245 0.6041 0.0411
-3.750 -0.1392 0.01773 0.01058 -0.0236 0.6005 0.0411
-3.500 -0.1131 0.01677 0.00947 -0.0231 0.5972 0.0413
-3.250 -0.0864 0.01601 0.00858 -0.0227 0.5934 0.0416
-3.000 -0.0594 0.01542 0.00786 -0.0223 0.5897 0.0420
-2.750 -0.0319 0.01463 0.00694 -0.0221 0.5862 0.0425
-2.500 -0.0045 0.01380 0.00607 -0.0220 0.5828 0.0436
-2.250 0.0226 0.01339 0.00568 -0.0218 0.5791 0.0448
-2.000 0.0497 0.01301 0.00528 -0.0215 0.5753 0.0458
-1.750 0.0765 0.01267 0.00491 -0.0211 0.5718 0.0468
-1.500 0.1030 0.01241 0.00459 -0.0207 0.5684 0.0480
-1.250 0.1296 0.01216 0.00433 -0.0203 0.5649 0.0491
-1.000 0.1554 0.01182 0.00398 -0.0198 0.5611 0.0507
-0.750 0.1807 0.01150 0.00369 -0.0192 0.5575 0.0534
-0.500 0.2069 0.01136 0.00353 -0.0187 0.5540 0.0565
-0.250 0.2329 0.01125 0.00337 -0.0182 0.5505 0.0595
0.000 0.2583 0.01100 0.00319 -0.0176 0.5468 0.0662
0.250 0.2839 0.01081 0.00306 -0.0170 0.5430 0.0779
0.500 0.3089 0.01060 0.00295 -0.0164 0.5394 0.1103
0.750 0.3324 0.01034 0.00292 -0.0155 0.5359 0.1904
1.000 0.3538 0.00993 0.00294 -0.0144 0.5324 0.3267
1.250 0.4426 0.00864 0.00346 -0.0272 0.5270 0.9459
1.500 0.4971 0.00913 0.00386 -0.0322 0.5226 0.9621
1.750 0.5558 0.00957 0.00421 -0.0384 0.5175 0.9738
2.000 0.6249 0.00976 0.00436 -0.0469 0.5111 0.9849
2.250 0.6829 0.00972 0.00422 -0.0533 0.5055 0.9928
2.500 0.7443 0.00942 0.00388 -0.0605 0.4997 1.0000
2.750 0.7688 0.00943 0.00390 -0.0599 0.4952 1.0000
3.000 0.7931 0.00947 0.00389 -0.0593 0.4907 1.0000
3.250 0.8173 0.00953 0.00393 -0.0587 0.4864 1.0000
3.500 0.8417 0.00955 0.00397 -0.0581 0.4812 1.0000
3.750 0.8659 0.00959 0.00400 -0.0575 0.4764 1.0000
4.000 0.8898 0.00969 0.00405 -0.0568 0.4718 1.0000
4.250 0.9141 0.00972 0.00413 -0.0562 0.4668 1.0000
4.500 0.9381 0.00977 0.00418 -0.0556 0.4615 1.0000
4.750 0.9617 0.00988 0.00425 -0.0549 0.4563 1.0000
5.000 0.9858 0.00993 0.00435 -0.0543 0.4507 1.0000
5.250 1.0094 0.01001 0.00442 -0.0536 0.4442 1.0000
5.500 1.0328 0.01010 0.00452 -0.0529 0.4368 1.0000
5.750 1.0562 0.01019 0.00462 -0.0522 0.4295 1.0000
6.000 1.0793 0.01032 0.00475 -0.0515 0.4234 1.0000
6.250 1.1026 0.01042 0.00488 -0.0508 0.4159 1.0000
6.500 1.1251 0.01058 0.00503 -0.0500 0.4088 1.0000
6.750 1.1480 0.01071 0.00519 -0.0493 0.4006 1.0000
7.000 1.1701 0.01089 0.00536 -0.0484 0.3925 1.0000
7.250 1.1923 0.01107 0.00556 -0.0475 0.3832 1.0000
7.500 1.2139 0.01127 0.00577 -0.0466 0.3729 1.0000
7.750 1.2346 0.01153 0.00600 -0.0456 0.3605 1.0000
8.000 1.2546 0.01184 0.00628 -0.0445 0.3482 1.0000
8.250 1.2745 0.01215 0.00658 -0.0434 0.3356 1.0000
8.500 1.2940 0.01247 0.00691 -0.0422 0.3234 1.0000
8.750 1.3123 0.01287 0.00728 -0.0408 0.3098 1.0000
9.000 1.3294 0.01332 0.00769 -0.0393 0.2960 1.0000
9.250 1.3453 0.01381 0.00816 -0.0377 0.2820 1.0000
9.500 1.3594 0.01438 0.00868 -0.0358 0.2668 1.0000
9.750 1.3722 0.01498 0.00924 -0.0337 0.2533 1.0000
10.000 1.3830 0.01563 0.00986 -0.0313 0.2404 1.0000
10.250 1.3908 0.01636 0.01056 -0.0286 0.2275 1.0000
10.500 1.3959 0.01712 0.01130 -0.0254 0.2156 1.0000
10.750 1.3918 0.01788 0.01206 -0.0206 0.2052 1.0000
11.000 1.3824 0.01910 0.01328 -0.0162 0.1950 1.0000
11.250 1.3770 0.02062 0.01477 -0.0130 0.1815 1.0000
11.500 1.3709 0.02247 0.01656 -0.0103 0.1638 1.0000
11.750 1.3569 0.02511 0.01906 -0.0076 0.1361 1.0000
12.250 1.3165 0.03203 0.02567 -0.0027 0.0834 1.0000
12.500 1.3093 0.03469 0.02834 -0.0013 0.0751 1.0000
12.750 1.3052 0.03715 0.03084 -0.0001 0.0667 1.0000
13.000 1.2998 0.03981 0.03350 0.0009 0.0582 1.0000
13.250 1.2899 0.04297 0.03661 0.0019 0.0451 1.0000
13.500 1.2809 0.04625 0.03983 0.0026 0.0356 1.0000
13.750 1.2744 0.04940 0.04299 0.0031 0.0309 1.0000
14.000 1.2712 0.05232 0.04595 0.0035 0.0282 1.0000
14.250 1.2663 0.05549 0.04917 0.0037 0.0263 1.0000
14.500 1.2610 0.05880 0.05253 0.0038 0.0248 1.0000
14.750 1.2580 0.06194 0.05575 0.0038 0.0239 1.0000
15.000 1.2564 0.06495 0.05884 0.0038 0.0230 1.0000
15.250 1.2494 0.06869 0.06265 0.0036 0.0220 1.0000
15.500 1.2437 0.07233 0.06635 0.0033 0.0214 1.0000
15.750 1.2333 0.07669 0.07078 0.0028 0.0207 1.0000
16.000 1.2298 0.08018 0.07437 0.0024 0.0205 1.0000
16.250 1.2269 0.08364 0.07791 0.0019 0.0200 1.0000
16.500 1.2232 0.08724 0.08159 0.0013 0.0194 1.0000
16.750 1.2191 0.09096 0.08538 0.0007 0.0192 1.0000
17.000 1.2136 0.09490 0.08939 -0.0001 0.0185 1.0000
17.250 1.2096 0.09864 0.09319 -0.0008 0.0184 1.0000
17.500 1.2052 0.10250 0.09712 -0.0016 0.0180 1.0000
17.750 1.2002 0.10640 0.10107 -0.0025 0.0177 1.0000
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