Fage & Collins 2 (fg2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 2 (fg2-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.64 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg2-il-1000000.txt Download as CSV file: xf-fg2-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 2
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4314 0.08769 0.08617 -0.0168 1.0000 0.0122
-8.000 -0.4447 0.08488 0.08340 -0.0172 1.0000 0.0122
-7.750 -0.4485 0.08149 0.08002 -0.0180 1.0000 0.0122
-7.500 -0.4481 0.07783 0.07637 -0.0193 1.0000 0.0122
-7.250 -0.4432 0.07346 0.07198 -0.0220 0.9996 0.0123
-7.000 -0.4165 0.06743 0.06589 -0.0298 0.9971 0.0123
-6.750 -0.3975 0.05948 0.05784 -0.0374 0.9946 0.0126
-6.500 -0.3759 0.05634 0.05466 -0.0402 0.9917 0.0128
-6.250 -0.3496 0.05290 0.05114 -0.0439 0.9887 0.0132
-6.000 -0.3212 0.04878 0.04691 -0.0481 0.9864 0.0137
-5.750 -0.2818 0.04267 0.04051 -0.0525 0.9845 0.0160
-5.500 -0.2633 0.03842 0.03608 -0.0524 0.9780 0.0161
-5.250 -0.2383 0.03332 0.03072 -0.0537 0.9743 0.0161
-4.750 -0.1985 0.02762 0.02473 -0.0538 0.9610 0.0174
-4.500 -0.1797 0.02650 0.02353 -0.0524 0.9485 0.0188
-4.250 -0.1513 0.02492 0.02161 -0.0505 0.9383 0.0210
-4.000 -0.1229 0.02205 0.01842 -0.0506 0.9303 0.0211
-3.750 -0.0944 0.01732 0.01331 -0.0519 0.9226 0.0223
-3.500 -0.0465 0.01620 0.01209 -0.0568 0.9141 0.0236
-3.250 0.0192 0.01664 0.01231 -0.0647 0.9020 0.0275
-3.000 0.0629 0.01541 0.01074 -0.0681 0.8798 0.0277
-2.750 0.0856 0.01227 0.00724 -0.0673 0.8545 0.0294
-2.500 0.1095 0.01172 0.00654 -0.0664 0.8178 0.0303
-2.250 0.1283 0.01141 0.00598 -0.0642 0.7622 0.0313
-2.000 0.1464 0.01125 0.00555 -0.0619 0.7069 0.0326
-1.750 0.1673 0.01114 0.00524 -0.0602 0.6675 0.0345
-1.500 0.1890 0.01059 0.00449 -0.0588 0.6392 0.0389
-1.250 0.2120 0.01023 0.00406 -0.0578 0.6165 0.0416
-1.000 0.2359 0.01002 0.00377 -0.0568 0.5978 0.0446
-0.750 0.2604 0.00949 0.00310 -0.0556 0.5810 0.0346
-0.500 0.2830 0.00916 0.00268 -0.0543 0.5624 0.0337
-0.250 0.3057 0.00892 0.00237 -0.0531 0.5459 0.0329
0.000 0.3289 0.00874 0.00213 -0.0519 0.5316 0.0330
0.250 0.3520 0.00859 0.00191 -0.0508 0.5167 0.0325
0.500 0.3755 0.00847 0.00172 -0.0497 0.5019 0.0325
0.750 0.3995 0.00840 0.00158 -0.0488 0.4877 0.0329
1.000 0.4235 0.00836 0.00148 -0.0479 0.4717 0.0339
1.250 0.4474 0.00838 0.00141 -0.0470 0.4529 0.0348
1.500 0.4717 0.00840 0.00137 -0.0463 0.4341 0.0355
1.750 0.4954 0.00849 0.00135 -0.0454 0.4096 0.0359
2.000 0.5196 0.00857 0.00135 -0.0446 0.3897 0.0362
2.250 0.5437 0.00866 0.00136 -0.0438 0.3722 0.0376
2.500 0.5683 0.00875 0.00139 -0.0431 0.3594 0.0391
2.750 0.7521 0.00735 0.00210 -0.0803 0.3331 1.0000
3.000 0.7760 0.00747 0.00218 -0.0794 0.3256 1.0000
3.250 0.8001 0.00757 0.00227 -0.0787 0.3194 1.0000
3.500 0.8239 0.00770 0.00236 -0.0778 0.3103 1.0000
3.750 0.8481 0.00781 0.00246 -0.0771 0.3025 1.0000
4.000 0.8717 0.00796 0.00257 -0.0763 0.2922 1.0000
4.250 0.8955 0.00810 0.00267 -0.0755 0.2803 1.0000
4.500 0.9189 0.00827 0.00278 -0.0746 0.2645 1.0000
4.750 0.9422 0.00844 0.00292 -0.0737 0.2467 1.0000
5.000 0.9616 0.00892 0.00313 -0.0722 0.1948 1.0000
5.250 0.9791 0.00955 0.00350 -0.0703 0.1474 1.0000
5.500 1.0002 0.00990 0.00377 -0.0691 0.1301 1.0000
5.750 1.0211 0.01027 0.00405 -0.0678 0.1109 1.0000
6.000 1.0367 0.01106 0.00452 -0.0657 0.0576 1.0000
6.250 1.0511 0.01197 0.00522 -0.0631 0.0172 1.0000
6.500 1.0719 0.01234 0.00563 -0.0618 0.0153 1.0000
6.750 1.0912 0.01283 0.00618 -0.0601 0.0129 1.0000
7.000 1.1113 0.01325 0.00668 -0.0586 0.0123 1.0000
7.250 1.1315 0.01364 0.00712 -0.0572 0.0117 1.0000
7.500 1.1508 0.01410 0.00764 -0.0557 0.0111 1.0000
7.750 1.1693 0.01461 0.00820 -0.0540 0.0104 1.0000
8.000 1.1868 0.01518 0.00883 -0.0521 0.0098 1.0000
8.250 1.2005 0.01602 0.00977 -0.0496 0.0091 1.0000
8.500 1.2084 0.01722 0.01111 -0.0460 0.0087 1.0000
8.750 1.2278 0.01758 0.01150 -0.0446 0.0084 1.0000
9.000 1.2431 0.01820 0.01219 -0.0425 0.0081 1.0000
9.250 1.2547 0.01902 0.01310 -0.0397 0.0080 1.0000
9.500 1.2680 0.01971 0.01385 -0.0373 0.0076 1.0000
9.750 1.2768 0.02065 0.01489 -0.0341 0.0075 1.0000
10.000 1.2896 0.02125 0.01553 -0.0316 0.0071 1.0000
10.250 1.2892 0.02226 0.01664 -0.0268 0.0071 1.0000
10.500 1.2972 0.02288 0.01731 -0.0236 0.0068 1.0000
10.750 1.3019 0.02376 0.01825 -0.0200 0.0066 1.0000
11.000 1.3052 0.02480 0.01936 -0.0165 0.0064 1.0000
11.250 1.3060 0.02609 0.02072 -0.0129 0.0063 1.0000
11.500 1.3073 0.02746 0.02219 -0.0097 0.0063 1.0000
11.750 1.2849 0.03133 0.02620 -0.0044 0.0058 1.0000
12.000 1.2891 0.03272 0.02769 -0.0024 0.0058 1.0000
12.250 1.2950 0.03393 0.02902 -0.0009 0.0056 1.0000
12.500 1.2970 0.03575 0.03095 0.0006 0.0056 1.0000
12.750 1.2984 0.03776 0.03308 0.0018 0.0055 1.0000
13.000 1.2973 0.04021 0.03565 0.0028 0.0054 1.0000
13.250 1.2915 0.04345 0.03903 0.0037 0.0054 1.0000
13.500 1.2899 0.04626 0.04198 0.0037 0.0052 1.0000
13.750 1.2888 0.04917 0.04500 0.0033 0.0051 1.0000
14.000 1.2825 0.05291 0.04888 0.0029 0.0051 1.0000
14.250 1.2743 0.05700 0.05311 0.0023 0.0051 1.0000
14.500 1.2650 0.06144 0.05771 0.0011 0.0050 1.0000
14.750 1.2537 0.06622 0.06263 -0.0001 0.0051 1.0000
15.000 1.2481 0.07034 0.06686 -0.0019 0.0050 1.0000
15.250 1.2323 0.07617 0.07285 -0.0039 0.0050 1.0000
15.500 1.2185 0.08184 0.07867 -0.0061 0.0050 1.0000
15.750 1.2001 0.08858 0.08557 -0.0089 0.0051 1.0000
16.000 1.1901 0.09416 0.09125 -0.0117 0.0050 1.0000
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Polar data table (+)
Polar graphs
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