RAF 33 AIRFOIL (raf33-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 33 AIRFOIL (raf33-il) Reynolds number: 200,000 Max Cl/Cd: 71.81 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf33-il-200000.txt Download as CSV file: xf-raf33-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2159 0.09995 0.09615 -0.0284 0.7573 0.0567
-9.750 -0.2323 0.09685 0.09305 -0.0327 0.7541 0.0585
-9.500 -0.2477 0.09359 0.08979 -0.0366 0.7509 0.0589
-9.250 -0.2419 0.08826 0.08447 -0.0370 0.7460 0.0596
-9.000 -0.2188 0.08501 0.08118 -0.0348 0.7398 0.0607
-8.750 -0.2103 0.08203 0.07815 -0.0347 0.7352 0.0618
-8.500 -0.2060 0.07887 0.07498 -0.0354 0.7306 0.0632
-8.250 -0.2050 0.07555 0.07167 -0.0365 0.7256 0.0647
-8.000 -0.2078 0.07211 0.06822 -0.0379 0.7213 0.0662
-7.750 -0.2219 0.06838 0.06448 -0.0409 0.7180 0.0680
-7.500 -0.2525 0.06530 0.06138 -0.0431 0.7143 0.0691
-7.250 -0.2765 0.06167 0.05755 -0.0445 0.7102 0.0698
-7.000 -0.2698 0.05588 0.05179 -0.0443 0.7062 0.0706
-6.750 -0.2831 0.06236 0.05789 -0.0475 0.7116 0.0711
-6.500 -0.2697 0.06004 0.05558 -0.0465 0.7066 0.0721
-6.250 -0.2570 0.05801 0.05348 -0.0456 0.7022 0.0739
-6.000 -0.2455 0.05578 0.05115 -0.0450 0.6979 0.0767
-5.750 -0.2447 0.05258 0.04737 -0.0442 0.6934 0.0830
-5.500 -0.2290 0.04935 0.04422 -0.0437 0.6889 0.0842
-5.250 -0.2128 0.04729 0.04213 -0.0427 0.6851 0.0855
-5.000 -0.1963 0.04549 0.04026 -0.0418 0.6809 0.0879
-4.750 -0.1846 0.04455 0.03865 -0.0393 0.6762 0.0970
-4.500 -0.1676 0.04085 0.03507 -0.0390 0.6719 0.0987
-4.250 -0.1483 0.03914 0.03335 -0.0382 0.6682 0.1011
-4.000 -0.1287 0.03779 0.03191 -0.0372 0.6642 0.1061
-3.750 -0.1129 0.03581 0.02958 -0.0354 0.6595 0.1146
-3.500 -0.0923 0.03416 0.02791 -0.0346 0.6552 0.1174
-3.250 -0.0745 0.02659 0.01872 -0.0291 0.6528 0.0706
-3.000 -0.0497 0.02562 0.01747 -0.0281 0.6494 0.0701
-2.750 -0.0251 0.02446 0.01616 -0.0273 0.6445 0.0700
-2.500 0.0009 0.02279 0.01429 -0.0268 0.6401 0.0693
-2.250 0.0280 0.02165 0.01292 -0.0263 0.6364 0.0694
-2.000 0.0558 0.02087 0.01189 -0.0259 0.6332 0.0698
-1.750 0.0844 0.01963 0.01064 -0.0262 0.6282 0.0712
-1.500 0.1120 0.01902 0.01006 -0.0261 0.6236 0.0741
-1.250 0.1400 0.01854 0.00952 -0.0259 0.6199 0.0770
-1.000 0.1683 0.01808 0.00895 -0.0257 0.6168 0.0798
-0.750 0.1947 0.01773 0.00864 -0.0254 0.6118 0.0828
-0.500 0.2201 0.01720 0.00822 -0.0249 0.6072 0.0884
-0.250 0.2463 0.01698 0.00794 -0.0243 0.6035 0.0965
0.000 0.2709 0.01657 0.00755 -0.0235 0.6005 0.1102
0.250 0.2925 0.01623 0.00745 -0.0224 0.5955 0.1395
0.500 0.3073 0.01534 0.00734 -0.0200 0.5911 0.3297
0.750 0.5562 0.01453 0.00775 -0.0634 0.5843 1.0000
1.000 0.5798 0.01467 0.00789 -0.0628 0.5791 1.0000
1.250 0.6038 0.01474 0.00792 -0.0622 0.5743 1.0000
1.500 0.6281 0.01476 0.00784 -0.0615 0.5704 1.0000
1.750 0.6526 0.01483 0.00780 -0.0608 0.5668 1.0000
2.000 0.6758 0.01498 0.00800 -0.0601 0.5610 1.0000
2.250 0.6999 0.01500 0.00797 -0.0594 0.5563 1.0000
2.500 0.7246 0.01500 0.00787 -0.0587 0.5526 1.0000
2.750 0.7478 0.01514 0.00804 -0.0580 0.5470 1.0000
3.000 0.7715 0.01518 0.00807 -0.0573 0.5414 1.0000
3.250 0.7962 0.01515 0.00795 -0.0566 0.5372 1.0000
3.500 0.8196 0.01527 0.00808 -0.0559 0.5320 1.0000
3.750 0.8428 0.01536 0.00820 -0.0551 0.5262 1.0000
4.000 0.8673 0.01535 0.00813 -0.0544 0.5218 1.0000
4.250 0.8910 0.01546 0.00824 -0.0537 0.5169 1.0000
4.500 0.9137 0.01559 0.00843 -0.0529 0.5108 1.0000
4.750 0.9380 0.01559 0.00838 -0.0522 0.5061 1.0000
5.000 0.9613 0.01571 0.00852 -0.0514 0.5008 1.0000
5.250 0.9836 0.01584 0.00872 -0.0506 0.4945 1.0000
5.500 1.0080 0.01586 0.00868 -0.0499 0.4897 1.0000
5.750 1.0302 0.01605 0.00895 -0.0490 0.4837 1.0000
6.000 1.0527 0.01616 0.00909 -0.0481 0.4773 1.0000
6.250 1.0774 0.01619 0.00904 -0.0475 0.4725 1.0000
6.500 1.0976 0.01641 0.00941 -0.0464 0.4646 1.0000
6.750 1.1213 0.01639 0.00935 -0.0455 0.4581 1.0000
7.000 1.1417 0.01657 0.00962 -0.0444 0.4495 1.0000
7.250 1.1647 0.01659 0.00959 -0.0435 0.4423 1.0000
7.500 1.1846 0.01683 0.00995 -0.0423 0.4339 1.0000
7.750 1.2069 0.01696 0.01006 -0.0414 0.4271 1.0000
8.000 1.2262 0.01724 0.01044 -0.0401 0.4184 1.0000
8.250 1.2480 0.01738 0.01054 -0.0391 0.4108 1.0000
8.500 1.2657 0.01770 0.01099 -0.0376 0.4012 1.0000
8.750 1.2857 0.01794 0.01121 -0.0364 0.3929 1.0000
9.000 1.3027 0.01824 0.01158 -0.0348 0.3826 1.0000
9.250 1.3188 0.01858 0.01197 -0.0331 0.3718 1.0000
9.500 1.3337 0.01891 0.01232 -0.0311 0.3600 1.0000
9.750 1.3480 0.01931 0.01269 -0.0292 0.3493 1.0000
10.000 1.3594 0.01981 0.01328 -0.0269 0.3382 1.0000
10.250 1.3690 0.02035 0.01386 -0.0244 0.3267 1.0000
10.500 1.3761 0.02098 0.01449 -0.0215 0.3159 1.0000
10.750 1.3796 0.02169 0.01521 -0.0182 0.3052 1.0000
11.000 1.3769 0.02243 0.01601 -0.0140 0.2961 1.0000
11.250 1.3740 0.02339 0.01694 -0.0103 0.2883 1.0000
11.500 1.3725 0.02454 0.01819 -0.0075 0.2786 1.0000
11.750 1.3716 0.02588 0.01956 -0.0051 0.2690 1.0000
12.000 1.3689 0.02747 0.02113 -0.0028 0.2587 1.0000
12.250 1.3670 0.02920 0.02295 -0.0011 0.2472 1.0000
12.500 1.3617 0.03131 0.02508 0.0006 0.2336 1.0000
12.750 1.3553 0.03367 0.02744 0.0021 0.2192 1.0000
13.000 1.3459 0.03642 0.03017 0.0034 0.2028 1.0000
13.250 1.3317 0.03976 0.03346 0.0046 0.1802 1.0000
13.500 1.3118 0.04378 0.03734 0.0056 0.1498 1.0000
13.750 1.2862 0.04861 0.04195 0.0062 0.1141 1.0000
14.000 1.2616 0.05369 0.04684 0.0066 0.0948 1.0000
14.250 1.2390 0.05883 0.05189 0.0066 0.0838 1.0000
14.500 1.2207 0.06372 0.05680 0.0065 0.0749 1.0000
14.750 1.2034 0.06869 0.06182 0.0061 0.0661 1.0000
15.000 1.1870 0.07372 0.06685 0.0056 0.0614 1.0000
15.250 1.1770 0.07806 0.07124 0.0051 0.0543 1.0000
15.500 1.1652 0.08265 0.07582 0.0044 0.0516 1.0000
15.750 1.1611 0.08634 0.07959 0.0039 0.0472 1.0000
16.000 1.1560 0.09012 0.08339 0.0034 0.0450 1.0000
16.250 1.1512 0.09376 0.08702 0.0029 0.0426 1.0000
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