Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 3 (fg3-il) Reynolds number: 200,000 Max Cl/Cd: 65.31 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg3-il-200000-n5.txt Download as CSV file: xf-fg3-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3247 0.10882 0.10547 -0.0317 1.0000 0.0203
-9.250 -0.3271 0.10627 0.10297 -0.0311 1.0000 0.0203
-9.000 -0.3331 0.10398 0.10075 -0.0302 1.0000 0.0203
-8.500 -0.3209 0.09636 0.09317 -0.0375 0.9948 0.0205
-8.250 -0.3110 0.09199 0.08881 -0.0423 0.9901 0.0205
-8.000 -0.3034 0.08766 0.08449 -0.0485 0.9831 0.0206
-7.750 -0.2923 0.08274 0.07956 -0.0544 0.9758 0.0206
-7.500 -0.2794 0.07797 0.07474 -0.0588 0.9689 0.0206
-7.250 -0.2690 0.07357 0.07030 -0.0618 0.9618 0.0206
-7.000 -0.2551 0.06943 0.06613 -0.0641 0.9572 0.0205
-6.750 -0.2455 0.06558 0.06223 -0.0652 0.9511 0.0203
-6.500 -0.2311 0.06202 0.05863 -0.0669 0.9460 0.0196
-6.250 -0.2135 0.05739 0.05390 -0.0702 0.9398 0.0192
-6.000 -0.1931 0.05284 0.04919 -0.0732 0.9331 0.0190
-5.500 -0.1428 0.04525 0.04123 -0.0783 0.9202 0.0238
-5.250 -0.1132 0.04014 0.03578 -0.0811 0.9159 0.0230
-5.000 -0.0908 0.03649 0.03183 -0.0813 0.9084 0.0232
-4.750 -0.0567 0.03271 0.02752 -0.0827 0.9031 0.0261
-4.250 -0.0036 0.02693 0.02099 -0.0833 0.8884 0.0282
-4.000 0.0208 0.02589 0.01985 -0.0833 0.8803 0.0310
-3.750 0.0483 0.02385 0.01742 -0.0830 0.8735 0.0319
-3.500 0.0681 0.02227 0.01552 -0.0810 0.8651 0.0321
-3.250 0.0975 0.02107 0.01393 -0.0809 0.8582 0.0339
-3.000 0.1173 0.02066 0.01323 -0.0786 0.8485 0.0352
-2.750 0.1424 0.01929 0.01161 -0.0779 0.8400 0.0353
-2.500 0.1674 0.01799 0.01010 -0.0771 0.8300 0.0356
-2.250 0.1894 0.01690 0.00889 -0.0757 0.8184 0.0364
-2.000 0.2131 0.01613 0.00806 -0.0748 0.8058 0.0382
-1.750 0.2388 0.01545 0.00726 -0.0741 0.7912 0.0384
-1.500 0.2659 0.01482 0.00651 -0.0737 0.7747 0.0384
-1.250 0.2938 0.01424 0.00582 -0.0734 0.7546 0.0387
-1.000 0.3204 0.01378 0.00524 -0.0729 0.7299 0.0391
-0.750 0.3459 0.01343 0.00474 -0.0722 0.6998 0.0396
-0.500 0.3686 0.01321 0.00433 -0.0709 0.6630 0.0401
-0.250 0.3883 0.01314 0.00404 -0.0690 0.6190 0.0420
0.000 0.4053 0.01319 0.00384 -0.0666 0.5734 0.0434
0.250 0.4214 0.01327 0.00367 -0.0641 0.5347 0.0437
0.500 0.4381 0.01338 0.00356 -0.0617 0.5032 0.0439
0.750 0.4565 0.01347 0.00347 -0.0597 0.4790 0.0442
1.000 0.4755 0.01358 0.00341 -0.0579 0.4590 0.0446
1.250 0.4955 0.01368 0.00337 -0.0562 0.4428 0.0452
1.750 0.5370 0.01389 0.00337 -0.0533 0.4161 0.0482
2.000 0.5581 0.01400 0.00341 -0.0520 0.4049 0.0521
2.250 0.7479 0.01293 0.00432 -0.0897 0.3778 1.0000
2.500 0.7695 0.01313 0.00445 -0.0885 0.3701 1.0000
2.750 0.7909 0.01335 0.00460 -0.0873 0.3637 1.0000
3.000 0.8129 0.01356 0.00476 -0.0862 0.3570 1.0000
3.250 0.8341 0.01380 0.00493 -0.0850 0.3513 1.0000
3.500 0.8563 0.01401 0.00513 -0.0839 0.3454 1.0000
3.750 0.8779 0.01424 0.00532 -0.0828 0.3395 1.0000
4.000 0.8992 0.01450 0.00554 -0.0816 0.3347 1.0000
4.250 0.9215 0.01471 0.00577 -0.0807 0.3295 1.0000
4.500 0.9433 0.01496 0.00602 -0.0796 0.3251 1.0000
4.750 0.9645 0.01525 0.00628 -0.0784 0.3212 1.0000
5.000 0.9869 0.01549 0.00656 -0.0775 0.3172 1.0000
5.250 1.0090 0.01574 0.00686 -0.0765 0.3130 1.0000
5.500 1.0306 0.01603 0.00717 -0.0755 0.3094 1.0000
5.750 1.0519 0.01636 0.00749 -0.0744 0.3060 1.0000
6.000 1.0741 0.01661 0.00784 -0.0735 0.3021 1.0000
6.250 1.0958 0.01689 0.00821 -0.0725 0.2981 1.0000
6.500 1.1153 0.01719 0.00851 -0.0711 0.2923 1.0000
6.750 1.1337 0.01739 0.00880 -0.0695 0.2824 1.0000
7.000 1.1508 0.01764 0.00907 -0.0676 0.2723 1.0000
7.250 1.1693 0.01791 0.00940 -0.0660 0.2646 1.0000
7.500 1.1867 0.01817 0.00975 -0.0642 0.2538 1.0000
7.750 1.2020 0.01846 0.01007 -0.0620 0.2403 1.0000
8.000 1.2147 0.01881 0.01040 -0.0594 0.2207 1.0000
8.250 1.2233 0.01941 0.01084 -0.0561 0.1814 1.0000
8.500 1.2029 0.02212 0.01261 -0.0488 0.0543 1.0000
8.750 1.2023 0.02362 0.01398 -0.0445 0.0257 1.0000
9.000 1.2109 0.02453 0.01499 -0.0416 0.0211 1.0000
9.250 1.2202 0.02540 0.01600 -0.0390 0.0191 1.0000
9.500 1.2282 0.02636 0.01711 -0.0363 0.0179 1.0000
9.750 1.2316 0.02765 0.01856 -0.0331 0.0162 1.0000
10.000 1.2336 0.02906 0.02015 -0.0300 0.0154 1.0000
10.250 1.2351 0.03053 0.02179 -0.0271 0.0144 1.0000
10.500 1.2384 0.03195 0.02335 -0.0246 0.0138 1.0000
10.750 1.2372 0.03376 0.02533 -0.0220 0.0131 1.0000
11.000 1.2353 0.03573 0.02745 -0.0197 0.0130 1.0000
11.250 1.2314 0.03800 0.02988 -0.0175 0.0125 1.0000
11.500 1.2257 0.04060 0.03264 -0.0157 0.0123 1.0000
11.750 1.2187 0.04354 0.03571 -0.0143 0.0120 1.0000
12.000 1.2112 0.04678 0.03908 -0.0134 0.0118 1.0000
12.250 1.2027 0.05038 0.04281 -0.0129 0.0115 1.0000
12.500 1.1957 0.05404 0.04660 -0.0128 0.0115 1.0000
12.750 1.1889 0.05785 0.05051 -0.0131 0.0112 1.0000
13.000 1.1806 0.06200 0.05476 -0.0135 0.0109 1.0000
13.250 1.1756 0.06575 0.05861 -0.0138 0.0109 1.0000
13.500 1.1703 0.06954 0.06249 -0.0142 0.0107 1.0000
13.750 1.1620 0.07330 0.06625 -0.0138 0.0101 1.0000
14.000 1.1621 0.07634 0.06937 -0.0139 0.0099 1.0000
14.250 1.1624 0.07967 0.07285 -0.0146 0.0095 1.0000
14.500 1.1640 0.08246 0.07575 -0.0144 0.0093 1.0000
14.750 1.1658 0.08524 0.07864 -0.0142 0.0091 1.0000
15.000 1.1673 0.08814 0.08164 -0.0142 0.0088 1.0000
15.250 1.1695 0.09090 0.08452 -0.0140 0.0087 1.0000
15.500 1.1711 0.09384 0.08758 -0.0140 0.0086 1.0000
15.750 1.1719 0.09698 0.09086 -0.0140 0.0085 1.0000
16.000 1.1708 0.10057 0.09459 -0.0148 0.0083 1.0000
16.250 1.1682 0.10443 0.09860 -0.0155 0.0081 1.0000
16.500 1.1654 0.10840 0.10272 -0.0165 0.0081 1.0000
16.750 1.1617 0.11259 0.10704 -0.0181 0.0078 1.0000
17.000 1.1564 0.11718 0.11179 -0.0196 0.0078 1.0000
17.250 1.1513 0.12180 0.11655 -0.0214 0.0077 1.0000
17.500 1.1440 0.12694 0.12185 -0.0236 0.0077 1.0000
17.750 1.1398 0.13140 0.12642 -0.0257 0.0075 1.0000
18.000 1.1333 0.13647 0.13159 -0.0282 0.0073 1.0000
18.250 1.1254 0.14202 0.13730 -0.0310 0.0072 1.0000
18.500 1.1190 0.14727 0.14265 -0.0337 0.0071 1.0000
18.750 1.1050 0.15486 0.15047 -0.0378 0.0073 1.0000
19.000 1.1032 0.15878 0.15439 -0.0400 0.0069 1.0000
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Polar data table (+)
Polar graphs
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