FX 83-W-108 (fx83w108-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX 83-W-108 (fx83w108-il) Reynolds number: 100,000 Max Cl/Cd: 60.98 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx83w108-il-100000.txt Download as CSV file: xf-fx83w108-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 83-W-108
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4230 0.10271 0.09824 -0.0286 1.0000 0.1259
-7.750 -0.4569 0.10258 0.09823 -0.0266 1.0000 0.1269
-7.500 -0.4965 0.10206 0.09785 -0.0268 1.0000 0.1275
-7.250 -0.4947 0.09834 0.09418 -0.0238 1.0000 0.1288
-7.000 -0.4684 0.09581 0.09160 -0.0186 1.0000 0.1333
-6.750 -0.4805 0.09429 0.09014 -0.0165 1.0000 0.1365
-6.500 -0.5007 0.08862 0.08452 -0.0313 0.9964 0.1435
-6.250 -0.4778 0.08735 0.08326 -0.0229 0.9949 0.1473
-6.000 -0.4619 0.08141 0.07726 -0.0352 0.9882 0.1598
-5.750 -0.4443 0.07936 0.07522 -0.0326 0.9841 0.1641
-5.500 -0.4100 0.05347 0.04812 -0.0716 0.9770 0.1122
-5.250 -0.3760 0.04090 0.03433 -0.0792 0.9747 0.0821
-5.000 -0.3428 0.03697 0.02985 -0.0823 0.9712 0.0806
-4.750 -0.3045 0.03464 0.02673 -0.0853 0.9679 0.0834
-4.500 -0.2781 0.03227 0.02392 -0.0860 0.9636 0.0847
-4.250 -0.2474 0.03032 0.02178 -0.0872 0.9599 0.0875
-4.000 -0.2114 0.02933 0.02058 -0.0891 0.9564 0.0944
-3.750 -0.1836 0.02821 0.01916 -0.0893 0.9519 0.0995
-3.500 -0.1557 0.02736 0.01834 -0.0897 0.9475 0.1075
-3.250 -0.1216 0.02655 0.01751 -0.0911 0.9439 0.1184
-3.000 -0.0904 0.02593 0.01693 -0.0920 0.9399 0.1334
-2.750 -0.0671 0.02540 0.01649 -0.0915 0.9346 0.1556
-2.500 -0.0359 0.02457 0.01613 -0.0926 0.9306 0.2230
-2.250 0.0003 0.02455 0.01671 -0.0944 0.9272 0.3824
-2.000 0.0153 0.02487 0.01703 -0.0923 0.9204 0.4272
-1.750 0.0444 0.02521 0.01736 -0.0927 0.9156 0.4696
-1.500 0.0810 0.02552 0.01771 -0.0943 0.9120 0.5086
-1.250 0.0933 0.02576 0.01798 -0.0918 0.9050 0.5362
-1.000 0.1216 0.02596 0.01827 -0.0919 0.9000 0.5722
-0.750 0.1592 0.02614 0.01851 -0.0936 0.8965 0.6092
-0.500 0.1692 0.02635 0.01878 -0.0908 0.8887 0.6332
-0.250 0.2020 0.02645 0.01894 -0.0918 0.8840 0.6666
0.000 0.2363 0.02658 0.01915 -0.0930 0.8796 0.7060
0.250 0.2542 0.02672 0.01945 -0.0917 0.8726 0.7492
0.500 0.3030 0.02619 0.01942 -0.0956 0.8687 1.0000
0.750 0.3448 0.02666 0.01961 -0.0992 0.8643 1.0000
1.000 0.3628 0.02726 0.02005 -0.0985 0.8561 1.0000
1.250 0.4030 0.02761 0.02027 -0.1009 0.8517 1.0000
1.500 0.4197 0.02829 0.02086 -0.0998 0.8436 1.0000
1.750 0.4530 0.02870 0.02119 -0.1010 0.8379 1.0000
2.000 0.4823 0.02919 0.02163 -0.1016 0.8315 1.0000
2.250 0.5065 0.02971 0.02211 -0.1014 0.8236 1.0000
2.500 0.5507 0.02986 0.02223 -0.1041 0.8197 1.0000
2.750 0.5610 0.03068 0.02304 -0.1018 0.8089 1.0000
3.000 0.6053 0.03072 0.02308 -0.1043 0.8046 1.0000
3.250 0.6183 0.03147 0.02385 -0.1024 0.7934 1.0000
3.500 0.6660 0.03124 0.02366 -0.1050 0.7890 1.0000
3.750 0.6809 0.03190 0.02434 -0.1032 0.7771 1.0000
4.000 0.7346 0.03122 0.02376 -0.1064 0.7732 1.0000
4.250 0.7513 0.03170 0.02428 -0.1046 0.7606 1.0000
4.500 0.8148 0.03015 0.02287 -0.1084 0.7569 1.0000
4.750 0.8394 0.03000 0.02280 -0.1072 0.7442 1.0000
5.000 0.8772 0.02903 0.02194 -0.1072 0.7325 1.0000
5.250 0.9690 0.02508 0.01820 -0.1135 0.7270 1.0000
5.500 1.0026 0.02410 0.01735 -0.1128 0.7134 1.0000
5.750 1.0429 0.02265 0.01603 -0.1128 0.6984 1.0000
6.000 1.0844 0.02113 0.01463 -0.1130 0.6810 1.0000
6.250 1.1047 0.02056 0.01417 -0.1103 0.6587 1.0000
6.500 1.1299 0.01969 0.01338 -0.1081 0.6305 1.0000
6.750 1.1475 0.01921 0.01291 -0.1048 0.5919 1.0000
7.000 1.1611 0.01904 0.01262 -0.1009 0.5366 1.0000
7.250 1.1668 0.01948 0.01252 -0.0959 0.4389 1.0000
7.500 1.1549 0.02102 0.01325 -0.0888 0.3348 1.0000
7.750 1.1422 0.02303 0.01458 -0.0825 0.2570 1.0000
8.000 1.1359 0.02507 0.01608 -0.0777 0.2058 1.0000
8.250 1.1376 0.02690 0.01761 -0.0741 0.1730 1.0000
8.500 1.1446 0.02859 0.01906 -0.0713 0.1504 1.0000
8.750 1.1572 0.03028 0.02049 -0.0693 0.1335 1.0000
9.000 1.1764 0.03188 0.02197 -0.0682 0.1195 1.0000
9.250 1.1955 0.03321 0.02336 -0.0670 0.1089 1.0000
9.500 1.2233 0.03493 0.02510 -0.0669 0.0995 1.0000
9.750 1.2603 0.03707 0.02707 -0.0685 0.0908 1.0000
10.000 1.2844 0.03875 0.02903 -0.0678 0.0854 1.0000
10.250 1.3226 0.04118 0.03143 -0.0698 0.0800 1.0000
10.500 1.3521 0.04415 0.03472 -0.0704 0.0763 1.0000
10.750 1.3652 0.04620 0.03711 -0.0683 0.0734 1.0000
11.000 1.3821 0.04881 0.04000 -0.0671 0.0712 1.0000
11.250 1.3987 0.05167 0.04310 -0.0660 0.0696 1.0000
11.500 1.4104 0.05468 0.04636 -0.0643 0.0683 1.0000
11.750 1.4210 0.05840 0.05028 -0.0630 0.0671 1.0000
12.000 1.4214 0.06327 0.05546 -0.0609 0.0660 1.0000
12.250 1.4058 0.06556 0.05809 -0.0559 0.0656 1.0000
12.500 1.3902 0.06858 0.06143 -0.0518 0.0654 1.0000
12.750 1.3716 0.07177 0.06493 -0.0480 0.0652 1.0000
13.000 1.3549 0.07584 0.06927 -0.0453 0.0654 1.0000
13.250 1.3373 0.08027 0.07394 -0.0432 0.0656 1.0000
13.500 1.3195 0.08521 0.07910 -0.0417 0.0659 1.0000
13.750 1.3021 0.09029 0.08441 -0.0407 0.0663 1.0000
14.000 1.2693 0.09418 0.08859 -0.0400 0.0669 1.0000
14.250 1.1301 0.11328 0.10837 -0.0495 0.0740 1.0000
14.500 1.0958 0.12431 0.11948 -0.0556 0.0762 1.0000
14.750 1.0811 0.13292 0.12812 -0.0595 0.0776 1.0000
15.000 1.0805 0.13942 0.13463 -0.0612 0.0784 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 83-W-108 (fx83w108-il)