Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 3 (fg3-il) Reynolds number: 200,000 Max Cl/Cd: 65.11 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg3-il-200000.txt Download as CSV file: xf-fg3-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 3
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3767 0.09292 0.08990 -0.0209 1.0000 0.0301
-7.500 -0.3925 0.09145 0.08849 -0.0186 1.0000 0.0301
-7.250 -0.4115 0.09009 0.08718 -0.0159 1.0000 0.0303
-7.000 -0.4237 0.08794 0.08508 -0.0148 1.0000 0.0307
-6.750 -0.4208 0.08440 0.08153 -0.0179 0.9981 0.0314
-6.500 -0.3868 0.07832 0.07526 -0.0319 0.9901 0.0328
-6.250 -0.3574 0.07324 0.06986 -0.0399 0.9835 0.0331
-6.000 -0.3465 0.06692 0.06367 -0.0409 0.9782 0.0339
-5.750 -0.3167 0.06299 0.05973 -0.0445 0.9736 0.0358
-5.500 -0.2896 0.05889 0.05549 -0.0483 0.9645 0.0380
-5.250 -0.2493 0.05549 0.05152 -0.0534 0.9551 0.0422
-5.000 -0.2259 0.04896 0.04489 -0.0565 0.9501 0.0437
-4.750 -0.2057 0.04604 0.04196 -0.0570 0.9427 0.0453
-4.500 -0.1768 0.04313 0.03890 -0.0589 0.9381 0.0491
-4.250 -0.1535 0.04043 0.03561 -0.0581 0.9309 0.0553
-4.000 -0.1287 0.03749 0.03280 -0.0596 0.9262 0.0592
-3.750 -0.0945 0.03512 0.02989 -0.0607 0.9227 0.0692
-3.500 -0.0755 0.03280 0.02765 -0.0601 0.9151 0.0733
-3.250 -0.0437 0.03062 0.02513 -0.0609 0.9107 0.0853
-3.000 -0.0068 0.02842 0.02272 -0.0631 0.9083 0.1005
-2.000 0.1085 0.02200 0.01607 -0.0655 0.8842 0.2223
-1.750 0.1482 0.02002 0.01419 -0.0681 0.8800 0.2721
-1.500 0.2210 0.01759 0.01012 -0.0694 0.8750 0.0750
-1.250 0.2612 0.01709 0.00931 -0.0707 0.8662 0.0678
-1.000 0.2922 0.01616 0.00831 -0.0708 0.8550 0.0674
-0.750 0.3255 0.01516 0.00729 -0.0714 0.8436 0.0671
-0.500 0.3547 0.01428 0.00641 -0.0712 0.8300 0.0662
-0.250 0.3781 0.01367 0.00580 -0.0697 0.8134 0.0659
0.000 0.4016 0.01313 0.00524 -0.0683 0.7943 0.0662
0.250 0.4252 0.01269 0.00475 -0.0669 0.7710 0.0666
0.500 0.4502 0.01233 0.00425 -0.0657 0.7400 0.0681
0.750 0.4754 0.01208 0.00377 -0.0647 0.6967 0.0734
1.000 0.4968 0.01214 0.00350 -0.0629 0.6407 0.0792
1.250 0.5127 0.01235 0.00338 -0.0601 0.5840 0.0889
1.500 0.6925 0.01167 0.00409 -0.0950 0.4929 1.0000
1.750 0.7120 0.01201 0.00423 -0.0933 0.4725 1.0000
2.000 0.7323 0.01234 0.00438 -0.0918 0.4562 1.0000
2.250 0.7534 0.01265 0.00454 -0.0905 0.4431 1.0000
2.500 0.7750 0.01299 0.00473 -0.0893 0.4320 1.0000
2.750 0.7971 0.01327 0.00493 -0.0882 0.4216 1.0000
3.000 0.8196 0.01357 0.00515 -0.0873 0.4125 1.0000
3.250 0.8424 0.01390 0.00536 -0.0864 0.4044 1.0000
3.500 0.8649 0.01416 0.00563 -0.0854 0.3961 1.0000
3.750 0.8884 0.01452 0.00588 -0.0847 0.3892 1.0000
4.000 0.9111 0.01479 0.00617 -0.0838 0.3825 1.0000
4.250 0.9346 0.01511 0.00645 -0.0831 0.3764 1.0000
4.500 0.9587 0.01548 0.00681 -0.0825 0.3710 1.0000
4.750 0.9818 0.01578 0.00715 -0.0817 0.3653 1.0000
5.000 1.0062 0.01614 0.00748 -0.0812 0.3606 1.0000
5.250 1.0303 0.01653 0.00790 -0.0807 0.3559 1.0000
5.500 1.0530 0.01685 0.00830 -0.0799 0.3507 1.0000
5.750 1.0773 0.01722 0.00867 -0.0794 0.3463 1.0000
6.000 1.1020 0.01767 0.00915 -0.0790 0.3421 1.0000
6.250 1.1206 0.01786 0.00944 -0.0773 0.3346 1.0000
6.500 1.1414 0.01816 0.00972 -0.0761 0.3273 1.0000
6.750 1.1592 0.01834 0.01003 -0.0743 0.3199 1.0000
7.000 1.1777 0.01857 0.01026 -0.0727 0.3119 1.0000
7.250 1.1939 0.01871 0.01051 -0.0705 0.3037 1.0000
7.500 1.2093 0.01887 0.01076 -0.0682 0.2947 1.0000
7.750 1.2239 0.01902 0.01093 -0.0658 0.2851 1.0000
8.000 1.2324 0.01904 0.01103 -0.0621 0.2705 1.0000
8.250 1.2410 0.01906 0.01118 -0.0584 0.2501 1.0000
8.500 1.2437 0.01930 0.01130 -0.0537 0.2083 1.0000
8.750 1.2255 0.02156 0.01264 -0.0464 0.0797 1.0000
9.000 1.2179 0.02353 0.01435 -0.0409 0.0435 1.0000
9.250 1.2235 0.02464 0.01562 -0.0374 0.0378 1.0000
9.500 1.2289 0.02574 0.01686 -0.0342 0.0344 1.0000
9.750 1.2257 0.02737 0.01865 -0.0300 0.0313 1.0000
10.000 1.2275 0.02872 0.02015 -0.0267 0.0306 1.0000
10.250 1.2287 0.03016 0.02175 -0.0236 0.0300 1.0000
10.500 1.2273 0.03186 0.02359 -0.0206 0.0292 1.0000
10.750 1.2236 0.03384 0.02571 -0.0176 0.0283 1.0000
11.000 1.2209 0.03587 0.02786 -0.0152 0.0282 1.0000
11.250 1.2154 0.03831 0.03041 -0.0129 0.0273 1.0000
11.500 1.2114 0.04077 0.03299 -0.0110 0.0271 1.0000
11.750 1.2062 0.04352 0.03582 -0.0094 0.0262 1.0000
12.000 1.2034 0.04618 0.03855 -0.0083 0.0256 1.0000
12.250 1.1973 0.04928 0.04167 -0.0071 0.0245 1.0000
12.500 1.1982 0.05173 0.04418 -0.0059 0.0243 1.0000
12.750 1.2064 0.05360 0.04601 -0.0037 0.0237 1.0000
13.000 1.2289 0.05486 0.04726 -0.0015 0.0234 1.0000
13.250 1.2400 0.05683 0.04936 -0.0003 0.0232 1.0000
13.500 1.2604 0.05871 0.05138 0.0009 0.0232 1.0000
13.750 1.2948 0.06093 0.05372 0.0019 0.0235 1.0000
14.000 1.3085 0.06445 0.05745 0.0027 0.0235 1.0000
14.250 1.3086 0.06720 0.06039 0.0038 0.0236 1.0000
14.500 1.3076 0.07104 0.06444 0.0046 0.0235 1.0000
14.750 1.3017 0.07395 0.06753 0.0054 0.0236 1.0000
15.000 1.2930 0.07694 0.07071 0.0058 0.0238 1.0000
15.250 1.2821 0.08098 0.07497 0.0059 0.0238 1.0000
15.500 1.2670 0.08391 0.07812 0.0052 0.0245 1.0000
15.750 1.2370 0.08989 0.08449 0.0030 0.0255 1.0000
16.000 1.2127 0.09647 0.09136 0.0004 0.0262 1.0000
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Polar data table (+)
Polar graphs
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