RAF 33 AIRFOIL (raf33-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 33 AIRFOIL (raf33-il) Reynolds number: 100,000 Max Cl/Cd: 48.24 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf33-il-100000-n5.txt Download as CSV file: xf-raf33-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2882 0.10421 0.09894 -0.0369 0.7668 0.0715
-9.500 -0.2983 0.10137 0.09613 -0.0409 0.7602 0.0720
-9.250 -0.3054 0.09805 0.09281 -0.0444 0.7536 0.0721
-9.000 -0.2905 0.09335 0.08811 -0.0433 0.7474 0.0728
-8.750 -0.2738 0.08999 0.08468 -0.0419 0.7420 0.0738
-8.500 -0.2658 0.08694 0.08161 -0.0422 0.7359 0.0747
-8.250 -0.2632 0.08388 0.07855 -0.0433 0.7299 0.0755
-8.000 -0.2654 0.08087 0.07551 -0.0443 0.7248 0.0760
-7.750 -0.2658 0.07823 0.07287 -0.0444 0.7189 0.0775
-7.500 -0.3029 0.07072 0.06507 -0.0492 0.7146 0.0605
-7.250 -0.2907 0.06806 0.06239 -0.0481 0.7098 0.0597
-7.000 -0.2828 0.06514 0.05941 -0.0476 0.7053 0.0586
-6.750 -0.2763 0.06194 0.05613 -0.0474 0.7000 0.0570
-6.500 -0.2710 0.05831 0.05233 -0.0472 0.6954 0.0553
-6.250 -0.2666 0.05401 0.04775 -0.0466 0.6916 0.0536
-6.000 -0.2618 0.04914 0.04251 -0.0457 0.6874 0.0523
-5.750 -0.2474 0.04714 0.04038 -0.0447 0.6822 0.0532
-5.500 -0.2338 0.04471 0.03772 -0.0435 0.6779 0.0540
-5.250 -0.2205 0.04190 0.03457 -0.0420 0.6745 0.0542
-5.000 -0.2068 0.03879 0.03109 -0.0403 0.6699 0.0537
-4.750 -0.1910 0.03614 0.02806 -0.0386 0.6651 0.0535
-4.500 -0.1733 0.03391 0.02544 -0.0370 0.6611 0.0536
-4.250 -0.1537 0.03202 0.02317 -0.0356 0.6577 0.0539
-4.000 -0.1323 0.03056 0.02144 -0.0345 0.6529 0.0548
-3.750 -0.1097 0.02933 0.01993 -0.0336 0.6482 0.0564
-3.500 -0.0862 0.02802 0.01827 -0.0326 0.6442 0.0578
-3.250 -0.0612 0.02674 0.01663 -0.0317 0.6409 0.0585
-3.000 -0.0353 0.02569 0.01533 -0.0313 0.6359 0.0593
-2.750 -0.0085 0.02477 0.01417 -0.0309 0.6314 0.0602
-2.500 0.0189 0.02386 0.01311 -0.0307 0.6275 0.0612
-2.250 0.0459 0.02315 0.01234 -0.0304 0.6243 0.0631
-2.000 0.0720 0.02276 0.01197 -0.0303 0.6191 0.0662
-1.750 0.0991 0.02228 0.01141 -0.0301 0.6146 0.0690
-1.500 0.1266 0.02175 0.01075 -0.0298 0.6109 0.0715
-1.250 0.1535 0.02117 0.01016 -0.0294 0.6078 0.0743
-1.000 0.1787 0.02090 0.00996 -0.0291 0.6026 0.0783
-0.750 0.2045 0.02067 0.00968 -0.0286 0.5981 0.0848
-0.500 0.2307 0.02033 0.00939 -0.0282 0.5944 0.0938
-0.250 0.2587 0.01999 0.00902 -0.0280 0.5914 0.1065
0.000 0.2854 0.01986 0.00901 -0.0281 0.5860 0.1316
0.250 0.3131 0.01951 0.00898 -0.0283 0.5815 0.1969
0.500 0.3325 0.01795 0.00875 -0.0271 0.5780 0.5793
0.750 0.5421 0.01807 0.00920 -0.0619 0.5713 1.0000
1.000 0.5654 0.01823 0.00931 -0.0613 0.5662 1.0000
1.250 0.5891 0.01832 0.00928 -0.0605 0.5621 1.0000
1.500 0.6131 0.01836 0.00919 -0.0597 0.5590 1.0000
1.750 0.6357 0.01863 0.00947 -0.0591 0.5534 1.0000
2.000 0.6588 0.01879 0.00959 -0.0583 0.5485 1.0000
2.250 0.6824 0.01886 0.00958 -0.0575 0.5447 1.0000
2.500 0.7056 0.01901 0.00968 -0.0567 0.5405 1.0000
2.750 0.7277 0.01930 0.01000 -0.0560 0.5346 1.0000
3.000 0.7508 0.01941 0.01006 -0.0551 0.5301 1.0000
3.250 0.7748 0.01942 0.00998 -0.0543 0.5265 1.0000
3.500 0.7955 0.01981 0.01046 -0.0534 0.5198 1.0000
3.750 0.8182 0.01993 0.01056 -0.0525 0.5146 1.0000
4.000 0.8423 0.01990 0.01046 -0.0516 0.5107 1.0000
4.250 0.8621 0.02031 0.01097 -0.0507 0.5034 1.0000
4.500 0.8846 0.02041 0.01105 -0.0497 0.4981 1.0000
4.750 0.9075 0.02050 0.01113 -0.0488 0.4933 1.0000
5.000 0.9271 0.02088 0.01160 -0.0477 0.4863 1.0000
5.250 0.9499 0.02095 0.01165 -0.0467 0.4813 1.0000
5.500 0.9704 0.02124 0.01200 -0.0457 0.4755 1.0000
5.750 0.9904 0.02155 0.01238 -0.0445 0.4690 1.0000
6.000 1.0136 0.02159 0.01239 -0.0436 0.4643 1.0000
6.250 1.0311 0.02208 0.01300 -0.0423 0.4571 1.0000
6.500 1.0520 0.02227 0.01323 -0.0411 0.4511 1.0000
6.750 1.0720 0.02254 0.01354 -0.0400 0.4452 1.0000
7.000 1.0896 0.02297 0.01407 -0.0385 0.4381 1.0000
7.250 1.1119 0.02305 0.01414 -0.0375 0.4330 1.0000
7.500 1.1261 0.02367 0.01492 -0.0358 0.4252 1.0000
7.750 1.1461 0.02388 0.01516 -0.0345 0.4191 1.0000
8.000 1.1611 0.02441 0.01578 -0.0328 0.4118 1.0000
8.250 1.1781 0.02474 0.01616 -0.0312 0.4045 1.0000
8.500 1.1921 0.02523 0.01674 -0.0294 0.3966 1.0000
8.750 1.2072 0.02558 0.01713 -0.0275 0.3885 1.0000
9.000 1.2174 0.02622 0.01785 -0.0253 0.3801 1.0000
9.250 1.2316 0.02659 0.01825 -0.0233 0.3724 1.0000
9.500 1.2374 0.02743 0.01921 -0.0206 0.3643 1.0000
9.750 1.2489 0.02796 0.01977 -0.0185 0.3575 1.0000
10.000 1.2491 0.02888 0.02076 -0.0150 0.3504 1.0000
10.250 1.2509 0.02973 0.02166 -0.0120 0.3435 1.0000
10.500 1.2535 0.03075 0.02273 -0.0095 0.3368 1.0000
10.750 1.2541 0.03206 0.02413 -0.0072 0.3301 1.0000
11.000 1.2646 0.03280 0.02491 -0.0055 0.3240 1.0000
11.250 1.2603 0.03466 0.02690 -0.0035 0.3167 1.0000
11.500 1.2698 0.03551 0.02774 -0.0020 0.3092 1.0000
11.750 1.2616 0.03786 0.03022 -0.0002 0.3003 1.0000
12.000 1.2635 0.03943 0.03181 0.0011 0.2915 1.0000
12.250 1.2607 0.04142 0.03382 0.0024 0.2808 1.0000
12.500 1.2530 0.04414 0.03665 0.0035 0.2716 1.0000
12.750 1.2490 0.04649 0.03900 0.0044 0.2607 1.0000
13.000 1.2442 0.04895 0.04144 0.0052 0.2491 1.0000
13.250 1.2339 0.05229 0.04490 0.0057 0.2387 1.0000
13.500 1.2258 0.05547 0.04814 0.0061 0.2281 1.0000
13.750 1.2191 0.05862 0.05132 0.0063 0.2170 1.0000
14.000 1.2112 0.06205 0.05476 0.0064 0.2050 1.0000
14.250 1.1998 0.06615 0.05893 0.0061 0.1916 1.0000
14.500 1.1896 0.07025 0.06310 0.0057 0.1778 1.0000
14.750 1.1785 0.07459 0.06746 0.0051 0.1603 1.0000
15.000 1.1660 0.07917 0.07200 0.0044 0.1360 1.0000
15.250 1.1474 0.08464 0.07725 0.0034 0.1090 1.0000
15.500 1.1285 0.09040 0.08287 0.0021 0.0968 1.0000
15.750 1.1118 0.09604 0.08843 0.0008 0.0893 1.0000
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