Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 3 (fg3-il) Reynolds number: 500,000 Max Cl/Cd: 89.03 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg3-il-500000-n5.txt Download as CSV file: xf-fg3-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2630 0.08321 0.08106 -0.0530 0.9810 0.0079
-8.000 -0.2604 0.07549 0.07337 -0.0584 0.9489 0.0079
-7.750 -0.2502 0.06954 0.06739 -0.0658 0.9376 0.0082
-7.500 -0.2275 0.06234 0.06010 -0.0761 0.9303 0.0083
-7.250 -0.2007 0.05436 0.05197 -0.0869 0.9237 0.0092
-7.000 -0.1640 0.04920 0.04664 -0.0954 0.9178 0.0094
-6.750 -0.1277 0.04499 0.04225 -0.1021 0.9122 0.0102
-6.500 -0.1003 0.03924 0.03620 -0.1070 0.9041 0.0107
-6.250 -0.0944 0.03111 0.02754 -0.1061 0.8946 0.0121
-6.000 -0.0699 0.02926 0.02548 -0.1067 0.8866 0.0124
-5.750 -0.0497 0.02870 0.02485 -0.1059 0.8785 0.0131
-5.500 -0.0326 0.02637 0.02225 -0.1043 0.8710 0.0139
-5.250 -0.0308 0.02125 0.01650 -0.0987 0.8619 0.0161
-5.000 -0.0102 0.02069 0.01583 -0.0975 0.8536 0.0165
-4.750 0.0120 0.02057 0.01566 -0.0966 0.8450 0.0172
-4.500 0.0298 0.01935 0.01423 -0.0945 0.8375 0.0182
-4.250 0.0479 0.01740 0.01182 -0.0918 0.8295 0.0201
-4.000 0.0662 0.01631 0.01050 -0.0898 0.8195 0.0211
-3.750 0.0875 0.01568 0.00978 -0.0885 0.8093 0.0217
-3.500 0.1091 0.01509 0.00907 -0.0872 0.7966 0.0222
-3.250 0.1307 0.01453 0.00836 -0.0858 0.7803 0.0229
-3.000 0.1527 0.01401 0.00767 -0.0843 0.7616 0.0240
-2.750 0.1742 0.01360 0.00705 -0.0828 0.7392 0.0250
-2.500 0.1950 0.01318 0.00639 -0.0811 0.7121 0.0255
-2.250 0.2150 0.01286 0.00585 -0.0792 0.6816 0.0258
-2.000 0.2336 0.01270 0.00546 -0.0771 0.6441 0.0262
-1.750 0.2502 0.01269 0.00520 -0.0745 0.5981 0.0266
-1.500 0.2663 0.01253 0.00477 -0.0720 0.5514 0.0272
-1.250 0.2832 0.01226 0.00428 -0.0696 0.5100 0.0275
-1.000 0.3020 0.01204 0.00391 -0.0677 0.4806 0.0277
-0.750 0.3213 0.01185 0.00360 -0.0659 0.4573 0.0281
-0.500 0.3413 0.01169 0.00335 -0.0643 0.4394 0.0285
-0.250 0.3616 0.01156 0.00315 -0.0627 0.4237 0.0292
0.000 0.3822 0.01149 0.00300 -0.0612 0.4094 0.0297
0.250 0.4032 0.01143 0.00287 -0.0597 0.3968 0.0301
0.500 0.4246 0.01137 0.00276 -0.0584 0.3855 0.0303
0.750 0.4462 0.01134 0.00268 -0.0570 0.3757 0.0310
1.000 0.4679 0.01134 0.00263 -0.0558 0.3670 0.0320
1.250 0.4901 0.01131 0.00257 -0.0546 0.3596 0.0323
1.500 0.5120 0.01133 0.00253 -0.0534 0.3521 0.0323
1.750 0.5344 0.01133 0.00251 -0.0523 0.3458 0.0327
2.000 0.5567 0.01137 0.00250 -0.0511 0.3395 0.0329
2.250 0.5788 0.01142 0.00251 -0.0500 0.3337 0.0333
2.500 0.6013 0.01147 0.00253 -0.0489 0.3279 0.0342
2.750 0.6230 0.01155 0.00257 -0.0477 0.3222 0.0350
3.000 0.6449 0.01161 0.00261 -0.0465 0.3172 0.0367
3.250 0.6667 0.01167 0.00267 -0.0453 0.3126 0.0401
3.750 0.9180 0.01092 0.00398 -0.0918 0.2938 1.0000
4.000 0.9398 0.01109 0.00413 -0.0906 0.2904 1.0000
4.250 0.9625 0.01122 0.00428 -0.0897 0.2871 1.0000
4.500 0.9847 0.01137 0.00444 -0.0887 0.2836 1.0000
4.750 1.0065 0.01155 0.00461 -0.0876 0.2800 1.0000
5.000 1.0276 0.01175 0.00480 -0.0864 0.2762 1.0000
5.250 1.0500 0.01190 0.00499 -0.0854 0.2717 1.0000
5.500 1.0714 0.01208 0.00517 -0.0842 0.2651 1.0000
5.750 1.0924 0.01228 0.00536 -0.0830 0.2572 1.0000
6.000 1.1125 0.01253 0.00557 -0.0817 0.2454 1.0000
6.250 1.1334 0.01273 0.00577 -0.0805 0.2361 1.0000
6.500 1.1532 0.01299 0.00601 -0.0791 0.2246 1.0000
6.750 1.1725 0.01328 0.00627 -0.0777 0.2138 1.0000
7.000 1.1892 0.01372 0.00660 -0.0758 0.1891 1.0000
7.250 1.1928 0.01504 0.00743 -0.0717 0.1131 1.0000
7.500 1.1845 0.01696 0.00885 -0.0654 0.0210 1.0000
7.750 1.1980 0.01744 0.00935 -0.0629 0.0157 1.0000
8.000 1.2129 0.01783 0.00980 -0.0606 0.0144 1.0000
8.250 1.2269 0.01828 0.01033 -0.0583 0.0127 1.0000
8.500 1.2397 0.01883 0.01094 -0.0558 0.0113 1.0000
8.750 1.2504 0.01951 0.01173 -0.0529 0.0101 1.0000
9.000 1.2632 0.02007 0.01237 -0.0505 0.0097 1.0000
9.250 1.2757 0.02065 0.01302 -0.0482 0.0090 1.0000
9.500 1.2867 0.02133 0.01378 -0.0457 0.0086 1.0000
9.750 1.2963 0.02210 0.01463 -0.0430 0.0080 1.0000
10.000 1.3059 0.02287 0.01547 -0.0405 0.0077 1.0000
10.250 1.3104 0.02397 0.01667 -0.0374 0.0071 1.0000
10.500 1.3170 0.02497 0.01776 -0.0348 0.0067 1.0000
10.750 1.3213 0.02617 0.01907 -0.0320 0.0065 1.0000
11.000 1.3269 0.02734 0.02033 -0.0296 0.0063 1.0000
11.250 1.3281 0.02884 0.02195 -0.0269 0.0061 1.0000
11.500 1.3301 0.03039 0.02361 -0.0245 0.0059 1.0000
11.750 1.3297 0.03219 0.02551 -0.0222 0.0058 1.0000
12.000 1.3301 0.03404 0.02747 -0.0203 0.0056 1.0000
12.250 1.3279 0.03623 0.02977 -0.0184 0.0054 1.0000
12.500 1.3254 0.03862 0.03229 -0.0170 0.0054 1.0000
12.750 1.3239 0.04108 0.03484 -0.0159 0.0052 1.0000
13.000 1.3169 0.04430 0.03817 -0.0151 0.0051 1.0000
13.250 1.3093 0.04785 0.04186 -0.0147 0.0051 1.0000
13.500 1.3034 0.05146 0.04558 -0.0148 0.0050 1.0000
13.750 1.2922 0.05599 0.05023 -0.0153 0.0049 1.0000
14.000 1.2846 0.06025 0.05460 -0.0162 0.0048 1.0000
14.250 1.2773 0.06465 0.05910 -0.0172 0.0045 1.0000
14.500 1.2601 0.07034 0.06491 -0.0183 0.0046 1.0000
14.750 1.2521 0.07483 0.06951 -0.0192 0.0046 1.0000
15.000 1.2443 0.07925 0.07403 -0.0201 0.0045 1.0000
15.250 1.2422 0.08305 0.07795 -0.0212 0.0044 1.0000
15.500 1.2339 0.08747 0.08244 -0.0220 0.0044 1.0000
15.750 1.2309 0.09141 0.08650 -0.0231 0.0042 1.0000
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Polar data table (+)
Polar graphs
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