Fage & Collins 2 (fg2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 2 (fg2-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.17 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg2-il-1000000-n5.txt Download as CSV file: xf-fg2-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4453 0.08826 0.08674 -0.0165 1.0000 0.0042
-8.500 -0.4485 0.08537 0.08388 -0.0169 1.0000 0.0043
-8.250 -0.4481 0.07913 0.07765 -0.0237 0.9976 0.0042
-8.000 -0.4269 0.07493 0.07344 -0.0304 0.9953 0.0047
-7.750 -0.4138 0.06750 0.06597 -0.0395 0.9917 0.0047
-7.500 -0.3976 0.05896 0.05733 -0.0490 0.9882 0.0052
-7.250 -0.3964 0.04454 0.04258 -0.0576 0.9813 0.0060
-7.000 -0.3754 0.03920 0.03704 -0.0602 0.9763 0.0063
-6.750 -0.3566 0.03733 0.03509 -0.0598 0.9688 0.0066
-6.250 -0.3563 0.02160 0.01821 -0.0528 0.9383 0.0088
-6.000 -0.3213 0.02109 0.01767 -0.0546 0.9307 0.0093
-5.750 -0.2846 0.01797 0.01418 -0.0571 0.9227 0.0106
-5.500 -0.2316 0.01558 0.01146 -0.0631 0.9133 0.0121
-5.250 -0.1671 0.01513 0.01085 -0.0717 0.8999 0.0132
-5.000 -0.1330 0.01211 0.00724 -0.0733 0.8774 0.0162
-4.750 -0.1027 0.01249 0.00750 -0.0738 0.8420 0.0165
-4.500 -0.0813 0.01264 0.00746 -0.0723 0.7941 0.0169
-4.250 -0.0633 0.01270 0.00727 -0.0701 0.7363 0.0173
-4.000 -0.0433 0.01278 0.00713 -0.0683 0.6908 0.0180
-3.750 -0.0219 0.01255 0.00670 -0.0669 0.6563 0.0188
-3.500 0.0006 0.01217 0.00612 -0.0657 0.6299 0.0197
-3.250 0.0239 0.01197 0.00575 -0.0646 0.6060 0.0205
-3.000 0.0479 0.01168 0.00533 -0.0637 0.5885 0.0210
-2.750 0.0722 0.01148 0.00501 -0.0629 0.5726 0.0213
-2.500 0.0967 0.01120 0.00462 -0.0621 0.5596 0.0215
-2.250 0.1212 0.01092 0.00425 -0.0613 0.5471 0.0216
-2.000 0.1463 0.01087 0.00413 -0.0607 0.5355 0.0218
-1.750 0.1685 0.00992 0.00312 -0.0595 0.5253 0.0226
-1.500 0.1920 0.00962 0.00277 -0.0585 0.5146 0.0231
-1.250 0.2160 0.00944 0.00255 -0.0577 0.5035 0.0238
-1.000 0.2401 0.00928 0.00236 -0.0568 0.4914 0.0242
-0.750 0.2638 0.00921 0.00221 -0.0559 0.4721 0.0249
-0.500 0.2880 0.00911 0.00205 -0.0551 0.4597 0.0253
-0.250 0.3118 0.00907 0.00193 -0.0542 0.4383 0.0258
0.000 0.3358 0.00901 0.00180 -0.0533 0.4216 0.0261
0.250 0.3593 0.00901 0.00169 -0.0524 0.3999 0.0261
0.500 0.3832 0.00902 0.00163 -0.0515 0.3796 0.0264
0.750 0.4075 0.00902 0.00157 -0.0508 0.3663 0.0268
1.000 0.4319 0.00903 0.00153 -0.0500 0.3544 0.0272
1.250 0.4564 0.00904 0.00149 -0.0493 0.3436 0.0273
1.500 0.4811 0.00905 0.00146 -0.0486 0.3338 0.0273
1.750 0.5058 0.00908 0.00145 -0.0480 0.3257 0.0273
2.000 0.5306 0.00910 0.00145 -0.0473 0.3173 0.0276
2.250 0.5555 0.00914 0.00147 -0.0467 0.3107 0.0276
2.500 0.5807 0.00917 0.00149 -0.0462 0.3052 0.0279
2.750 0.6056 0.00924 0.00153 -0.0456 0.2987 0.0284
3.000 0.6309 0.00928 0.00157 -0.0450 0.2942 0.0291
3.250 0.6561 0.00932 0.00162 -0.0445 0.2893 0.0331
3.750 0.8571 0.00815 0.00247 -0.0795 0.2536 1.0000
4.000 0.8796 0.00838 0.00259 -0.0785 0.2281 1.0000
4.250 0.8972 0.00900 0.00288 -0.0767 0.1654 1.0000
4.500 0.9178 0.00939 0.00314 -0.0753 0.1390 1.0000
4.750 0.9394 0.00970 0.00337 -0.0741 0.1210 1.0000
5.000 0.9614 0.00998 0.00358 -0.0731 0.1080 1.0000
5.250 0.9836 0.01025 0.00380 -0.0720 0.0959 1.0000
5.750 1.0176 0.01163 0.00478 -0.0681 0.0151 1.0000
6.000 1.0393 0.01192 0.00509 -0.0669 0.0126 1.0000
6.250 1.0605 0.01227 0.00547 -0.0657 0.0097 1.0000
6.500 1.0824 0.01253 0.00577 -0.0646 0.0090 1.0000
6.750 1.1037 0.01283 0.00611 -0.0635 0.0081 1.0000
7.000 1.1244 0.01318 0.00648 -0.0622 0.0073 1.0000
7.250 1.1436 0.01365 0.00699 -0.0606 0.0063 1.0000
7.500 1.1641 0.01399 0.00738 -0.0593 0.0061 1.0000
7.750 1.1841 0.01436 0.00780 -0.0580 0.0057 1.0000
8.000 1.2038 0.01474 0.00822 -0.0566 0.0052 1.0000
8.250 1.2231 0.01514 0.00864 -0.0551 0.0048 1.0000
8.500 1.2402 0.01569 0.00923 -0.0533 0.0042 1.0000
8.750 1.2573 0.01623 0.00984 -0.0515 0.0041 1.0000
9.000 1.2740 0.01678 0.01046 -0.0496 0.0040 1.0000
9.250 1.2915 0.01723 0.01098 -0.0479 0.0037 1.0000
9.500 1.3065 0.01785 0.01167 -0.0458 0.0036 1.0000
9.750 1.3216 0.01844 0.01233 -0.0437 0.0034 1.0000
10.000 1.3340 0.01917 0.01315 -0.0411 0.0034 1.0000
10.250 1.3474 0.01979 0.01383 -0.0388 0.0032 1.0000
10.500 1.3600 0.02033 0.01442 -0.0364 0.0030 1.0000
10.750 1.3664 0.02100 0.01516 -0.0327 0.0030 1.0000
11.000 1.3735 0.02167 0.01587 -0.0294 0.0028 1.0000
11.250 1.3784 0.02249 0.01681 -0.0258 0.0028 1.0000
11.500 1.3782 0.02367 0.01809 -0.0217 0.0026 1.0000
11.750 1.3799 0.02481 0.01934 -0.0182 0.0025 1.0000
12.000 1.3819 0.02603 0.02065 -0.0150 0.0026 1.0000
12.250 1.3887 0.02703 0.02174 -0.0127 0.0025 1.0000
12.500 1.3878 0.02862 0.02346 -0.0099 0.0024 1.0000
12.750 1.3889 0.03022 0.02516 -0.0077 0.0024 1.0000
13.000 1.3951 0.03156 0.02659 -0.0063 0.0023 1.0000
13.250 1.3843 0.03452 0.02970 -0.0043 0.0023 1.0000
13.500 1.3819 0.03705 0.03236 -0.0034 0.0022 1.0000
13.750 1.3748 0.04039 0.03583 -0.0031 0.0022 1.0000
14.000 1.3824 0.04227 0.03780 -0.0033 0.0021 1.0000
14.250 1.3707 0.04672 0.04239 -0.0041 0.0021 1.0000
14.500 1.3591 0.05142 0.04724 -0.0052 0.0021 1.0000
14.750 1.3510 0.05576 0.05170 -0.0065 0.0021 1.0000
15.000 1.3340 0.06140 0.05750 -0.0082 0.0021 1.0000
15.250 1.3326 0.06498 0.06116 -0.0094 0.0020 1.0000
15.500 1.3326 0.06841 0.06466 -0.0107 0.0019 1.0000
15.750 1.3044 0.07600 0.07243 -0.0132 0.0020 1.0000
16.000 1.2846 0.08260 0.07917 -0.0155 0.0020 1.0000
16.250 1.2785 0.08730 0.08394 -0.0174 0.0019 1.0000
16.500 1.2694 0.09252 0.08926 -0.0195 0.0019 1.0000
16.750 1.2520 0.09918 0.09604 -0.0221 0.0019 1.0000
17.000 1.2409 0.10494 0.10189 -0.0245 0.0019 1.0000
17.250 1.2267 0.11126 0.10831 -0.0270 0.0019 1.0000
17.500 1.2138 0.11749 0.11465 -0.0297 0.0019 1.0000
17.750 1.1979 0.12437 0.12164 -0.0326 0.0019 1.0000
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Polar data table (+)
Polar graphs
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