Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 3 (fg3-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.33 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg3-il-1000000-n5.txt Download as CSV file: xf-fg3-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2867 0.09210 0.09047 -0.0511 0.9893 0.0045
-9.500 -0.2649 0.08976 0.08813 -0.0553 0.9867 0.0050
-9.000 -0.2758 0.08116 0.07956 -0.0573 0.9430 0.0048
-8.750 -0.2507 0.07602 0.07439 -0.0659 0.9354 0.0051
-8.500 -0.2229 0.06952 0.06785 -0.0782 0.9284 0.0057
-8.250 -0.2033 0.05108 0.04912 -0.1066 0.9119 0.0066
-7.750 -0.1483 0.04396 0.04171 -0.1171 0.8937 0.0071
-7.500 -0.1389 0.03958 0.03713 -0.1181 0.8839 0.0074
-7.000 -0.1581 0.02637 0.02312 -0.1102 0.8687 0.0092
-6.750 -0.1399 0.02540 0.02204 -0.1088 0.8613 0.0095
-6.250 -0.1325 0.01769 0.01350 -0.1001 0.8486 0.0121
-6.000 -0.1109 0.01726 0.01298 -0.0990 0.8413 0.0123
-5.750 -0.0872 0.01731 0.01302 -0.0982 0.8331 0.0126
-5.500 -0.0649 0.01713 0.01276 -0.0971 0.8233 0.0131
-5.250 -0.0556 0.01339 0.00841 -0.0931 0.8138 0.0159
-5.000 -0.0335 0.01317 0.00811 -0.0918 0.8020 0.0161
-4.750 -0.0104 0.01339 0.00830 -0.0908 0.7881 0.0164
-4.500 0.0111 0.01337 0.00821 -0.0894 0.7709 0.0167
-4.250 0.0317 0.01317 0.00787 -0.0879 0.7497 0.0172
-4.000 0.0516 0.01297 0.00751 -0.0861 0.7261 0.0178
-3.750 0.0718 0.01259 0.00694 -0.0843 0.7018 0.0187
-3.500 0.0916 0.01212 0.00623 -0.0825 0.6745 0.0196
-3.250 0.1102 0.01194 0.00582 -0.0804 0.6363 0.0201
-3.000 0.1285 0.01200 0.00563 -0.0782 0.5893 0.0205
-2.750 0.1459 0.01181 0.00517 -0.0760 0.5388 0.0209
-2.500 0.1656 0.01139 0.00458 -0.0743 0.5048 0.0213
-2.250 0.1856 0.01123 0.00425 -0.0727 0.4704 0.0215
-2.000 0.2071 0.01108 0.00399 -0.0713 0.4474 0.0218
-1.750 0.2290 0.01090 0.00372 -0.0701 0.4296 0.0220
-1.500 0.2512 0.01078 0.00353 -0.0689 0.4140 0.0225
-1.250 0.2735 0.01065 0.00333 -0.0677 0.4007 0.0229
-1.000 0.2954 0.01049 0.00310 -0.0664 0.3883 0.0232
-0.750 0.3174 0.01036 0.00291 -0.0651 0.3768 0.0236
-0.250 0.3619 0.01016 0.00260 -0.0627 0.3585 0.0247
0.000 0.3841 0.01011 0.00250 -0.0615 0.3505 0.0252
0.250 0.4070 0.01003 0.00239 -0.0604 0.3441 0.0255
0.500 0.4292 0.00998 0.00230 -0.0593 0.3372 0.0256
0.750 0.4522 0.00993 0.00223 -0.0582 0.3317 0.0259
1.000 0.4749 0.00991 0.00217 -0.0571 0.3258 0.0261
1.250 0.4976 0.00991 0.00215 -0.0561 0.3197 0.0264
1.500 0.5209 0.00991 0.00213 -0.0551 0.3150 0.0266
1.750 0.5435 0.00990 0.00210 -0.0540 0.3096 0.0267
2.000 0.5660 0.00991 0.00208 -0.0529 0.3047 0.0268
2.250 0.5891 0.00990 0.00207 -0.0520 0.3009 0.0268
2.500 0.6117 0.00990 0.00205 -0.0509 0.2965 0.0273
2.750 0.6338 0.00993 0.00205 -0.0497 0.2925 0.0281
3.000 0.6559 0.00995 0.00206 -0.0485 0.2892 0.0292
3.250 0.6781 0.00998 0.00209 -0.0474 0.2858 0.0307
3.500 0.6998 0.01003 0.00215 -0.0462 0.2819 0.0320
3.750 0.7213 0.01010 0.00221 -0.0449 0.2783 0.0335
4.000 0.7431 0.01017 0.00228 -0.0437 0.2751 0.0349
4.250 0.9995 0.00940 0.00351 -0.0980 0.2604 1.0000
4.500 1.0226 0.00951 0.00363 -0.0971 0.2565 1.0000
4.750 1.0440 0.00971 0.00377 -0.0960 0.2465 1.0000
5.000 1.0663 0.00986 0.00391 -0.0950 0.2388 1.0000
5.250 1.0877 0.01006 0.00407 -0.0938 0.2315 1.0000
5.500 1.1093 0.01024 0.00423 -0.0927 0.2222 1.0000
5.750 1.1305 0.01044 0.00441 -0.0915 0.2146 1.0000
6.000 1.1507 0.01071 0.00462 -0.0902 0.2027 1.0000
6.250 1.1686 0.01110 0.00489 -0.0884 0.1790 1.0000
6.500 1.1726 0.01238 0.00571 -0.0842 0.1030 1.0000
6.750 1.1746 0.01387 0.00679 -0.0795 0.0205 1.0000
7.000 1.1931 0.01423 0.00715 -0.0779 0.0143 1.0000
7.250 1.2117 0.01456 0.00749 -0.0763 0.0124 1.0000
7.500 1.2293 0.01494 0.00790 -0.0745 0.0101 1.0000
7.750 1.2471 0.01526 0.00825 -0.0728 0.0095 1.0000
8.000 1.2632 0.01557 0.00859 -0.0707 0.0089 1.0000
8.250 1.2773 0.01592 0.00898 -0.0683 0.0082 1.0000
8.500 1.2904 0.01633 0.00942 -0.0656 0.0073 1.0000
8.750 1.3033 0.01676 0.00989 -0.0630 0.0068 1.0000
9.000 1.3177 0.01712 0.01029 -0.0607 0.0064 1.0000
9.250 1.3313 0.01755 0.01077 -0.0584 0.0059 1.0000
9.500 1.3455 0.01795 0.01120 -0.0562 0.0056 1.0000
9.750 1.3579 0.01847 0.01177 -0.0538 0.0052 1.0000
10.000 1.3698 0.01902 0.01237 -0.0513 0.0051 1.0000
10.250 1.3774 0.01983 0.01326 -0.0482 0.0046 1.0000
10.500 1.3910 0.02032 0.01378 -0.0462 0.0044 1.0000
10.750 1.4000 0.02107 0.01462 -0.0435 0.0043 1.0000
11.000 1.4127 0.02164 0.01522 -0.0415 0.0041 1.0000
11.250 1.4190 0.02259 0.01627 -0.0387 0.0040 1.0000
11.500 1.4304 0.02327 0.01700 -0.0368 0.0037 1.0000
11.750 1.4328 0.02455 0.01839 -0.0338 0.0037 1.0000
12.000 1.4437 0.02531 0.01919 -0.0321 0.0035 1.0000
12.250 1.4485 0.02653 0.02048 -0.0297 0.0034 1.0000
12.500 1.4546 0.02770 0.02172 -0.0277 0.0033 1.0000
12.750 1.4565 0.02923 0.02332 -0.0254 0.0031 1.0000
13.000 1.4537 0.03121 0.02541 -0.0230 0.0030 1.0000
13.250 1.4547 0.03300 0.02730 -0.0211 0.0031 1.0000
13.500 1.4498 0.03542 0.02984 -0.0193 0.0030 1.0000
13.750 1.4445 0.03809 0.03263 -0.0177 0.0029 1.0000
14.000 1.4447 0.04036 0.03499 -0.0168 0.0029 1.0000
14.250 1.4488 0.04238 0.03709 -0.0163 0.0027 1.0000
14.500 1.4327 0.04685 0.04172 -0.0158 0.0028 1.0000
14.750 1.4260 0.05054 0.04552 -0.0159 0.0027 1.0000
15.000 1.4136 0.05526 0.05038 -0.0165 0.0027 1.0000
15.250 1.4087 0.05918 0.05440 -0.0173 0.0026 1.0000
15.500 1.3900 0.06528 0.06065 -0.0188 0.0027 1.0000
15.750 1.3841 0.06952 0.06498 -0.0199 0.0027 1.0000
16.000 1.3615 0.07632 0.07193 -0.0217 0.0027 1.0000
16.250 1.3474 0.08183 0.07754 -0.0232 0.0025 1.0000
16.500 1.3309 0.08768 0.08350 -0.0247 0.0026 1.0000
16.750 1.3275 0.09161 0.08750 -0.0259 0.0025 1.0000
17.000 1.3140 0.09711 0.09310 -0.0274 0.0024 1.0000
17.250 1.3006 0.10259 0.09868 -0.0290 0.0025 1.0000
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Polar data table (+)
Polar graphs
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