FX 83-W-227 (fx83w227-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 83-W-227 (fx83w227-il) Reynolds number: 100,000 Max Cl/Cd: 8.94 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx83w227-il-100000.txt Download as CSV file: xf-fx83w227-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 83-W-227
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5791 0.09732 0.09216 -0.0737 0.9896 0.1365
-12.750 -0.6472 0.08306 0.07773 -0.0811 0.9846 0.1351
-12.500 -0.7197 0.07250 0.06687 -0.0851 0.9774 0.1335
-12.250 -0.7720 0.06602 0.06003 -0.0860 0.9698 0.1331
-12.000 -0.8119 0.06247 0.05620 -0.0828 0.9594 0.1333
-11.750 -0.8451 0.06012 0.05357 -0.0778 0.9497 0.1336
-11.500 -0.8654 0.05754 0.05063 -0.0743 0.9421 0.1346
-11.250 -0.8895 0.05573 0.04851 -0.0685 0.9318 0.1355
-11.000 -0.8848 0.05298 0.04540 -0.0675 0.9261 0.1373
-10.750 -0.8792 0.05178 0.04423 -0.0650 0.9175 0.1392
-10.500 -0.8529 0.05056 0.04298 -0.0660 0.9123 0.1424
-10.250 -0.8432 0.04926 0.04150 -0.0643 0.9062 0.1452
-10.000 -0.8453 0.04804 0.04002 -0.0606 0.8976 0.1475
-9.750 -0.8319 0.04639 0.03788 -0.0595 0.8927 0.1506
-9.500 -0.8274 0.04537 0.03694 -0.0565 0.8846 0.1529
-9.250 -0.8029 0.04450 0.03608 -0.0567 0.8791 0.1568
-9.000 -0.7723 0.04331 0.03469 -0.0579 0.8752 0.1620
-8.750 -0.7815 0.04292 0.03408 -0.0523 0.8657 0.1642
-8.500 -0.7547 0.04173 0.03287 -0.0528 0.8607 0.1688
-8.250 -0.7182 0.04087 0.03200 -0.0548 0.8573 0.1754
-8.000 -0.7245 0.04070 0.03168 -0.0496 0.8483 0.1787
-7.750 -0.7011 0.03980 0.03071 -0.0494 0.8427 0.1843
-7.500 -0.6627 0.03899 0.02995 -0.0515 0.8392 0.1925
-7.250 -0.6661 0.03899 0.02977 -0.0468 0.8311 0.1971
-7.000 -0.6442 0.03835 0.02925 -0.0463 0.8249 0.2040
-6.750 -0.6118 0.03769 0.02846 -0.0473 0.8209 0.2147
-6.500 -0.5677 0.03676 0.02769 -0.0503 0.8185 0.2275
-6.250 -0.5925 0.03731 0.02819 -0.0422 0.8071 0.2303
-6.000 -0.5600 0.03660 0.02758 -0.0431 0.8028 0.2435
-5.750 -0.5205 0.03580 0.02686 -0.0452 0.8000 0.2609
-5.500 -0.5422 0.03644 0.02747 -0.0377 0.7893 0.2661
-5.250 -0.5172 0.03594 0.02708 -0.0374 0.7845 0.2841
-5.000 -0.4818 0.03519 0.02647 -0.0386 0.7815 0.3099
-4.750 -0.4976 0.03572 0.02710 -0.0322 0.7714 0.3203
-4.500 -0.4797 0.03537 0.02691 -0.0307 0.7661 0.3482
-4.250 -0.4496 0.03468 0.02650 -0.0307 0.7628 0.3890
-4.000 -0.4610 0.03517 0.02717 -0.0249 0.7535 0.4116
-3.750 -0.4482 0.03505 0.02730 -0.0224 0.7476 0.4530
-3.500 -0.4206 0.03481 0.02729 -0.0216 0.7441 0.5044
-3.250 -0.4239 0.03551 0.02813 -0.0169 0.7360 0.5338
-3.000 -0.4136 0.03593 0.02865 -0.0139 0.7291 0.5670
-2.750 -0.3821 0.03601 0.02877 -0.0135 0.7253 0.6040
-2.500 -0.3416 0.03607 0.02884 -0.0142 0.7230 0.6364
-2.250 -0.3723 0.03756 0.03041 -0.0064 0.7108 0.6481
-2.000 -0.3398 0.03774 0.03057 -0.0060 0.7067 0.6739
-1.750 -0.2992 0.03773 0.03052 -0.0068 0.7043 0.6989
-1.500 -0.3275 0.03932 0.03218 0.0005 0.6925 0.7101
-1.250 -0.2979 0.03954 0.03238 0.0011 0.6884 0.7304
-1.000 -0.2570 0.03949 0.03230 0.0004 0.6858 0.7508
-0.750 -0.2853 0.04091 0.03374 0.0075 0.6742 0.7651
-0.500 -0.2583 0.04115 0.03395 0.0084 0.6700 0.7834
-0.250 -0.2188 0.04116 0.03394 0.0078 0.6673 0.8016
0.000 -0.2375 0.04270 0.03555 0.0132 0.6569 0.8151
0.250 -0.2101 0.04298 0.03582 0.0138 0.6518 0.8335
0.500 -0.1659 0.04301 0.03581 0.0124 0.6490 0.8522
0.750 -0.1111 0.04299 0.03572 0.0095 0.6471 0.8693
1.000 -0.1455 0.04543 0.03824 0.0155 0.6341 0.8853
1.250 -0.0739 0.04596 0.03871 0.0089 0.6310 0.8959
1.500 -0.0059 0.04593 0.03857 0.0033 0.6290 0.9063
1.750 -0.0143 0.04914 0.04185 0.0041 0.6165 0.9174
2.000 0.0499 0.04954 0.04216 -0.0019 0.6131 0.9245
2.250 0.1294 0.04947 0.04199 -0.0099 0.6110 0.9289
2.500 0.1907 0.04892 0.04135 -0.0145 0.6096 0.9380
2.750 0.1791 0.05315 0.04566 -0.0148 0.5951 0.9464
3.000 0.2380 0.05278 0.04522 -0.0195 0.5929 0.9548
3.250 0.3114 0.05204 0.04441 -0.0263 0.5915 0.9594
3.500 0.2909 0.05649 0.04893 -0.0256 0.5770 0.9709
3.750 0.3517 0.05617 0.04856 -0.0311 0.5748 0.9774
4.000 0.4158 0.05540 0.04775 -0.0366 0.5732 0.9833
4.250 0.4847 0.05419 0.04648 -0.0426 0.5722 0.9887
4.500 0.4624 0.05978 0.05217 -0.0432 0.5566 0.9991
4.750 0.4543 0.06084 0.05320 -0.0401 0.5515 1.0000
5.000 0.3809 0.06417 0.05653 -0.0309 0.5409 1.0000
5.250 0.3860 0.06314 0.05542 -0.0272 0.5380 1.0000
5.500 0.3313 0.06590 0.05812 -0.0195 0.5295 1.0000
5.750 0.3201 0.06764 0.05980 -0.0164 0.5239 1.0000
6.000 0.3416 0.06777 0.05985 -0.0154 0.5206 1.0000
6.250 0.3781 0.06707 0.05907 -0.0154 0.5184 1.0000
6.500 0.3238 0.07248 0.06449 -0.0108 0.5077 1.0000
6.750 0.3382 0.07354 0.06551 -0.0100 0.5038 1.0000
7.000 0.3704 0.07343 0.06535 -0.0099 0.5011 1.0000
7.250 0.4144 0.07253 0.06439 -0.0103 0.4993 1.0000
7.500 0.3425 0.07973 0.07164 -0.0061 0.4883 1.0000
7.750 0.3636 0.08057 0.07246 -0.0057 0.4848 1.0000
8.000 0.4035 0.08007 0.07191 -0.0060 0.4822 1.0000
8.250 0.3606 0.08555 0.07743 -0.0035 0.4747 1.0000
8.500 0.3152 0.09740 0.08943 -0.0053 0.5165 1.0000
8.750 0.3052 0.10015 0.09219 -0.0042 0.5159 1.0000
9.000 0.2844 0.10180 0.09386 -0.0021 0.5080 1.0000
9.250 0.3089 0.10320 0.09525 -0.0023 0.5026 1.0000
9.500 0.3625 0.10527 0.09729 -0.0041 0.4988 1.0000
9.750 0.3150 0.10750 0.09956 -0.0013 0.4931 1.0000
10.000 0.3291 0.10901 0.10107 -0.0011 0.4864 1.0000
10.250 0.3708 0.11067 0.10272 -0.0021 0.4823 1.0000
10.500 0.3777 0.11366 0.10572 -0.0021 0.4802 1.0000
10.750 0.3572 0.11478 0.10686 -0.0004 0.4691 1.0000
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Polar data table (+)
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