Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 4 (fg4-il) Reynolds number: 200,000 Max Cl/Cd: 65.44 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg4-il-200000.txt Download as CSV file: xf-fg4-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 4
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3249 0.10778 0.10441 -0.0210 1.0000 0.0429
-9.000 -0.3291 0.10568 0.10236 -0.0200 1.0000 0.0433
-8.750 -0.3349 0.10358 0.10031 -0.0190 1.0000 0.0438
-8.500 -0.3216 0.09994 0.09668 -0.0233 0.9968 0.0448
-8.250 -0.3082 0.09592 0.09266 -0.0293 0.9920 0.0460
-8.000 -0.3093 0.09148 0.08820 -0.0399 0.9831 0.0471
-7.750 -0.3073 0.08498 0.08154 -0.0524 0.9702 0.0475
-7.500 -0.2856 0.08213 0.07881 -0.0494 0.9685 0.0481
-7.250 -0.2614 0.07876 0.07545 -0.0515 0.9652 0.0489
-7.000 -0.2459 0.07533 0.07200 -0.0538 0.9570 0.0500
-6.750 -0.2275 0.07127 0.06790 -0.0577 0.9489 0.0512
-6.500 -0.2018 0.06643 0.06292 -0.0640 0.9429 0.0533
-6.250 -0.1878 0.06068 0.05676 -0.0692 0.9314 0.0553
-6.000 -0.1688 0.05765 0.05382 -0.0693 0.9247 0.0560
-5.750 -0.1436 0.05473 0.05090 -0.0709 0.9194 0.0572
-5.500 -0.1120 0.05142 0.04748 -0.0740 0.9163 0.0594
-5.000 -0.0648 0.04453 0.04009 -0.0763 0.9023 0.0652
-4.750 -0.0435 0.04228 0.03784 -0.0761 0.8940 0.0667
-4.500 -0.0130 0.04105 0.03593 -0.0762 0.8880 0.0745
-4.250 0.0224 0.03670 0.03180 -0.0796 0.8860 0.0766
-4.000 0.0441 0.03495 0.03003 -0.0790 0.8753 0.0796
-3.750 0.0811 0.03274 0.02738 -0.0807 0.8703 0.0883
-3.500 0.1045 0.03075 0.02544 -0.0804 0.8585 0.0913
-3.250 0.1474 0.02888 0.02322 -0.0833 0.8520 0.1032
-3.000 0.1672 0.02724 0.02161 -0.0819 0.8364 0.1077
-2.750 0.1843 0.02613 0.02027 -0.0794 0.8203 0.1201
-2.500 0.2074 0.02497 0.01908 -0.0784 0.8045 0.1288
-2.250 0.2309 0.02356 0.01756 -0.0776 0.7889 0.1436
-1.750 0.3119 0.00835 0.00218 -0.0816 0.7315 0.2282
-1.500 0.3296 0.00725 0.00119 -0.0803 0.7163 0.2549
-1.250 0.3716 0.01848 0.01087 -0.0787 0.7235 0.1038
-1.000 0.4097 0.01794 0.00978 -0.0786 0.7058 0.0739
-0.750 0.4409 0.01667 0.00839 -0.0790 0.6861 0.0698
-0.500 0.4700 0.01613 0.00765 -0.0787 0.6710 0.0665
-0.250 0.4961 0.01579 0.00716 -0.0778 0.6554 0.0653
0.250 0.5406 0.01518 0.00648 -0.0749 0.6264 0.0677
0.500 0.5589 0.01498 0.00626 -0.0726 0.6120 0.0693
0.750 0.5784 0.01481 0.00604 -0.0706 0.5993 0.0697
1.000 0.5956 0.01467 0.00583 -0.0681 0.5849 0.0709
1.250 0.6116 0.01457 0.00568 -0.0653 0.5710 0.0724
1.500 0.6260 0.01452 0.00556 -0.0622 0.5568 0.0741
1.750 0.6414 0.01443 0.00542 -0.0594 0.5437 0.0781
2.000 0.6570 0.01444 0.00534 -0.0566 0.5300 0.0843
2.250 0.6723 0.01434 0.00531 -0.0537 0.5167 0.1207
2.500 0.9122 0.01395 0.00649 -0.1015 0.4567 1.0000
2.750 0.9266 0.01416 0.00659 -0.0987 0.4383 1.0000
3.000 0.9373 0.01442 0.00669 -0.0951 0.4135 1.0000
3.250 0.9492 0.01467 0.00682 -0.0918 0.3942 1.0000
3.500 0.9602 0.01497 0.00697 -0.0884 0.3728 1.0000
3.750 0.9726 0.01529 0.00716 -0.0853 0.3530 1.0000
4.000 0.9856 0.01563 0.00738 -0.0824 0.3352 1.0000
4.250 0.9992 0.01599 0.00763 -0.0796 0.3185 1.0000
4.500 1.0132 0.01635 0.00789 -0.0770 0.3048 1.0000
5.000 1.0437 0.01704 0.00845 -0.0723 0.2781 1.0000
5.250 1.0587 0.01742 0.00877 -0.0699 0.2646 1.0000
5.500 1.0733 0.01782 0.00910 -0.0675 0.2508 1.0000
5.750 1.0876 0.01825 0.00945 -0.0652 0.2376 1.0000
6.000 1.1018 0.01870 0.00984 -0.0628 0.2242 1.0000
6.250 1.1176 0.01909 0.01022 -0.0608 0.2130 1.0000
6.500 1.1290 0.01969 0.01070 -0.0581 0.1938 1.0000
6.750 1.1421 0.02024 0.01117 -0.0557 0.1787 1.0000
7.000 1.1526 0.02093 0.01175 -0.0530 0.1562 1.0000
7.250 1.1603 0.02180 0.01247 -0.0499 0.1308 1.0000
7.500 1.1648 0.02289 0.01336 -0.0465 0.1034 1.0000
7.750 1.1729 0.02379 0.01418 -0.0438 0.0910 1.0000
8.000 1.1821 0.02465 0.01502 -0.0412 0.0856 1.0000
8.250 1.1931 0.02543 0.01582 -0.0390 0.0835 1.0000
8.500 1.2033 0.02627 0.01668 -0.0368 0.0818 1.0000
8.750 1.2127 0.02718 0.01763 -0.0345 0.0803 1.0000
9.000 1.2230 0.02805 0.01856 -0.0325 0.0798 1.0000
9.250 1.2320 0.02904 0.01961 -0.0304 0.0791 1.0000
9.500 1.2399 0.03011 0.02077 -0.0284 0.0783 1.0000
9.750 1.2475 0.03125 0.02198 -0.0264 0.0778 1.0000
10.000 1.2529 0.03258 0.02338 -0.0243 0.0770 1.0000
10.250 1.2590 0.03391 0.02478 -0.0225 0.0767 1.0000
10.500 1.2645 0.03534 0.02629 -0.0208 0.0766 1.0000
10.750 1.2683 0.03695 0.02799 -0.0191 0.0763 1.0000
11.000 1.2731 0.03856 0.02968 -0.0176 0.0762 1.0000
11.250 1.2766 0.04035 0.03155 -0.0162 0.0760 1.0000
11.500 1.2789 0.04233 0.03360 -0.0150 0.0756 1.0000
11.750 1.2814 0.04435 0.03569 -0.0139 0.0753 1.0000
12.000 1.2842 0.04640 0.03781 -0.0129 0.0750 1.0000
12.250 1.2867 0.04853 0.04000 -0.0121 0.0746 1.0000
12.500 1.2893 0.05070 0.04223 -0.0113 0.0742 1.0000
12.750 1.2895 0.05309 0.04463 -0.0105 0.0731 1.0000
13.000 1.2929 0.05516 0.04670 -0.0097 0.0723 1.0000
13.250 1.2988 0.05703 0.04864 -0.0091 0.0720 1.0000
13.500 1.3049 0.05895 0.05063 -0.0086 0.0717 1.0000
13.750 1.3111 0.06085 0.05262 -0.0082 0.0714 1.0000
14.000 1.3174 0.06275 0.05459 -0.0078 0.0710 1.0000
14.250 1.3236 0.06468 0.05661 -0.0074 0.0707 1.0000
14.500 1.3294 0.06668 0.05869 -0.0071 0.0702 1.0000
14.750 1.3351 0.06871 0.06079 -0.0069 0.0697 1.0000
15.000 1.3392 0.07094 0.06311 -0.0068 0.0689 1.0000
15.250 1.3461 0.07282 0.06506 -0.0066 0.0686 1.0000
15.500 1.3510 0.07495 0.06726 -0.0065 0.0679 1.0000
15.750 1.3584 0.07676 0.06914 -0.0063 0.0677 1.0000
16.000 1.3633 0.07888 0.07129 -0.0062 0.0666 1.0000
16.250 1.3708 0.08070 0.07319 -0.0061 0.0665 1.0000
16.500 1.3825 0.08184 0.07428 -0.0055 0.0653 1.0000
16.750 1.3948 0.08297 0.07544 -0.0049 0.0647 1.0000
17.000 1.3976 0.08542 0.07801 -0.0049 0.0639 1.0000
17.250 1.3975 0.08831 0.08104 -0.0055 0.0637 1.0000
17.500 1.3937 0.09177 0.08466 -0.0064 0.0633 1.0000
17.750 1.3887 0.09545 0.08850 -0.0075 0.0627 1.0000
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Polar data table (+)
Polar graphs
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