Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 4 (fg4-il) Reynolds number: 500,000 Max Cl/Cd: 62.16 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg4-il-500000.txt Download as CSV file: xf-fg4-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 4
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1226 0.08927 0.08702 -0.0606 0.9777 0.0271
-9.750 -0.1112 0.08565 0.08340 -0.0628 0.9764 0.0272
-9.500 -0.0994 0.08197 0.07973 -0.0652 0.9753 0.0275
-9.250 -0.0958 0.07883 0.07660 -0.0658 0.9694 0.0279
-9.000 -0.0870 0.07499 0.07277 -0.0683 0.9669 0.0282
-8.750 -0.0774 0.07091 0.06869 -0.0713 0.9651 0.0287
-8.500 -0.0774 0.06767 0.06546 -0.0719 0.9577 0.0290
-8.250 -0.0704 0.06334 0.06114 -0.0754 0.9547 0.0296
-8.000 -0.0752 0.05906 0.05687 -0.0783 0.9467 0.0302
-7.750 -0.0897 0.05325 0.05101 -0.0852 0.9395 0.0306
-7.500 -0.0937 0.04604 0.04359 -0.0919 0.9326 0.0308
-7.250 -0.0830 0.04077 0.03825 -0.0941 0.9301 0.0310
-7.000 -0.0691 0.03791 0.03539 -0.0944 0.9245 0.0312
-6.750 -0.0487 0.03475 0.03218 -0.0962 0.9204 0.0314
-6.500 -0.0220 0.03129 0.02864 -0.0996 0.9176 0.0317
-6.250 0.0045 0.02802 0.02527 -0.1027 0.9129 0.0323
-6.000 0.0310 0.02480 0.02191 -0.1055 0.9067 0.0331
-5.750 0.0020 0.03781 0.03465 -0.1007 0.9101 0.0330
-5.500 0.0337 0.03390 0.02993 -0.1018 0.9038 0.0356
-5.250 0.0710 0.02998 0.02606 -0.1064 0.8994 0.0361
-5.000 0.0941 0.02851 0.02455 -0.1064 0.8899 0.0365
-4.750 0.1293 0.02688 0.02279 -0.1090 0.8809 0.0372
-4.500 0.1599 0.02535 0.02109 -0.1101 0.8690 0.0384
-4.250 0.1658 0.02553 0.02066 -0.1034 0.8527 0.0411
-4.000 0.1684 0.02276 0.01791 -0.0990 0.8362 0.0417
-3.750 0.1764 0.02177 0.01688 -0.0949 0.8152 0.0422
-3.500 0.1871 0.02090 0.01589 -0.0913 0.7862 0.0428
-3.250 0.2038 0.02013 0.01490 -0.0888 0.7543 0.0438
-3.000 0.2213 0.02106 0.01524 -0.0851 0.7251 0.0474
-2.750 0.2325 0.01866 0.01270 -0.0822 0.7002 0.0485
-2.500 0.2486 0.01797 0.01190 -0.0798 0.6791 0.0495
-2.250 0.2646 0.01744 0.01124 -0.0771 0.6610 0.0507
-2.000 0.2778 0.01725 0.01068 -0.0733 0.6441 0.0558
-1.750 0.2948 0.01634 0.00977 -0.0712 0.6280 0.0574
-1.500 0.3112 0.01596 0.00929 -0.0686 0.6116 0.0599
-1.250 0.3272 0.01555 0.00869 -0.0658 0.5988 0.0657
-1.000 0.3445 0.01508 0.00818 -0.0635 0.5840 0.0684
-0.250 0.4105 0.01350 0.00588 -0.0572 0.5471 0.0477
0.000 0.4360 0.01258 0.00495 -0.0564 0.5353 0.0434
0.250 0.4577 0.01229 0.00455 -0.0547 0.5234 0.0419
0.500 0.4768 0.01212 0.00433 -0.0527 0.5098 0.0419
0.750 0.4955 0.01202 0.00417 -0.0505 0.4973 0.0418
1.000 0.5129 0.01190 0.00399 -0.0482 0.4804 0.0420
1.250 0.5301 0.01182 0.00387 -0.0458 0.4628 0.0425
1.500 0.5472 0.01181 0.00379 -0.0434 0.4447 0.0432
1.750 0.5623 0.01188 0.00376 -0.0407 0.4159 0.0437
2.000 0.5756 0.01211 0.00382 -0.0377 0.3801 0.0458
2.250 0.5896 0.01237 0.00388 -0.0348 0.3450 0.0470
2.500 0.6050 0.01264 0.00398 -0.0323 0.3138 0.0470
2.750 0.6227 0.01280 0.00402 -0.0303 0.2910 0.0506
3.000 0.6388 0.01313 0.00417 -0.0281 0.2592 0.0522
3.250 0.6558 0.01342 0.00432 -0.0260 0.2331 0.0569
3.500 0.9240 0.01489 0.00683 -0.0828 0.0625 1.0000
3.750 0.9413 0.01515 0.00707 -0.0807 0.0616 1.0000
4.000 0.9585 0.01542 0.00734 -0.0787 0.0608 1.0000
4.250 0.9753 0.01573 0.00766 -0.0765 0.0599 1.0000
4.500 0.9924 0.01604 0.00796 -0.0745 0.0594 1.0000
4.750 1.0082 0.01640 0.00833 -0.0723 0.0585 1.0000
5.000 1.0246 0.01673 0.00867 -0.0702 0.0583 1.0000
5.250 1.0401 0.01712 0.00907 -0.0679 0.0577 1.0000
5.500 1.0543 0.01758 0.00955 -0.0655 0.0571 1.0000
5.750 1.0683 0.01805 0.01003 -0.0631 0.0567 1.0000
6.000 1.0833 0.01846 0.01047 -0.0609 0.0564 1.0000
6.250 1.0980 0.01890 0.01092 -0.0587 0.0563 1.0000
6.500 1.1115 0.01941 0.01145 -0.0564 0.0560 1.0000
6.750 1.1248 0.01992 0.01199 -0.0540 0.0560 1.0000
7.000 1.1377 0.02047 0.01257 -0.0517 0.0560 1.0000
7.250 1.1504 0.02104 0.01318 -0.0494 0.0558 1.0000
7.500 1.1617 0.02170 0.01387 -0.0470 0.0556 1.0000
7.750 1.1727 0.02239 0.01459 -0.0446 0.0556 1.0000
8.000 1.1828 0.02315 0.01539 -0.0422 0.0554 1.0000
8.250 1.1929 0.02394 0.01623 -0.0399 0.0554 1.0000
8.500 1.2025 0.02479 0.01712 -0.0377 0.0554 1.0000
8.750 1.2114 0.02572 0.01809 -0.0354 0.0553 1.0000
9.000 1.2209 0.02664 0.01905 -0.0334 0.0552 1.0000
9.250 1.2290 0.02769 0.02015 -0.0313 0.0550 1.0000
9.500 1.2372 0.02877 0.02127 -0.0293 0.0545 1.0000
9.750 1.2454 0.02988 0.02243 -0.0275 0.0543 1.0000
10.000 1.2515 0.03119 0.02379 -0.0256 0.0535 1.0000
10.250 1.2589 0.03246 0.02510 -0.0239 0.0533 1.0000
10.500 1.2653 0.03385 0.02653 -0.0223 0.0530 1.0000
10.750 1.2713 0.03532 0.02806 -0.0208 0.0527 1.0000
11.000 1.2775 0.03684 0.02962 -0.0195 0.0525 1.0000
11.250 1.2825 0.03850 0.03133 -0.0182 0.0520 1.0000
11.500 1.2876 0.04023 0.03310 -0.0170 0.0518 1.0000
11.750 1.2904 0.04217 0.03505 -0.0158 0.0511 1.0000
12.000 1.2984 0.04371 0.03665 -0.0149 0.0513 1.0000
12.250 1.3034 0.04551 0.03847 -0.0139 0.0509 1.0000
12.500 1.3102 0.04714 0.04011 -0.0128 0.0505 1.0000
12.750 1.3204 0.04847 0.04143 -0.0116 0.0501 1.0000
13.000 1.3273 0.05017 0.04320 -0.0110 0.0497 1.0000
13.250 1.3295 0.05245 0.04561 -0.0109 0.0493 1.0000
13.500 1.3346 0.05448 0.04773 -0.0107 0.0490 1.0000
13.750 1.3404 0.05645 0.04977 -0.0104 0.0487 1.0000
14.000 1.3454 0.05855 0.05194 -0.0103 0.0484 1.0000
14.250 1.3490 0.06085 0.05433 -0.0103 0.0478 1.0000
14.500 1.3525 0.06320 0.05675 -0.0103 0.0473 1.0000
14.750 1.3569 0.06542 0.05904 -0.0103 0.0470 1.0000
15.000 1.3585 0.06808 0.06177 -0.0106 0.0462 1.0000
15.250 1.3612 0.07058 0.06433 -0.0108 0.0458 1.0000
15.500 1.3609 0.07353 0.06731 -0.0113 0.0448 1.0000
15.750 1.3652 0.07575 0.06956 -0.0113 0.0445 1.0000
16.000 1.3729 0.07712 0.07091 -0.0104 0.0435 1.0000
16.250 1.3710 0.08052 0.07443 -0.0114 0.0433 1.0000
16.500 1.3667 0.08446 0.07852 -0.0128 0.0428 1.0000
16.750 1.3660 0.08781 0.08197 -0.0138 0.0425 1.0000
17.000 1.3597 0.09228 0.08659 -0.0156 0.0416 1.0000
17.250 1.3586 0.09569 0.09009 -0.0167 0.0411 1.0000
17.500 1.3552 0.09966 0.09417 -0.0181 0.0405 1.0000
17.750 1.3512 0.10381 0.09841 -0.0198 0.0398 1.0000
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Polar data table (+)
Polar graphs
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