Fage & Collins 1 (fg1-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 1 (fg1-il) Reynolds number: 200,000 Max Cl/Cd: 78.07 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg1-il-200000.txt Download as CSV file: xf-fg1-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 1
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4129 0.08937 0.08580 -0.0257 1.0000 0.0384
-8.250 -0.4218 0.08715 0.08365 -0.0247 1.0000 0.0388
-8.000 -0.4360 0.08530 0.08187 -0.0227 1.0000 0.0392
-7.750 -0.4466 0.08301 0.07963 -0.0216 1.0000 0.0397
-7.500 -0.4553 0.08050 0.07715 -0.0210 1.0000 0.0404
-7.250 -0.4611 0.07769 0.07433 -0.0216 1.0000 0.0413
-7.000 -0.4630 0.07415 0.07057 -0.0271 1.0000 0.0427
-6.750 -0.4645 0.06960 0.06597 -0.0265 1.0000 0.0432
-6.500 -0.4619 0.06664 0.06308 -0.0242 1.0000 0.0437
-6.250 -0.4577 0.06420 0.06066 -0.0223 1.0000 0.0444
-6.000 -0.4518 0.06171 0.05815 -0.0211 1.0000 0.0452
-5.750 -0.4442 0.05914 0.05553 -0.0203 1.0000 0.0464
-5.500 -0.4344 0.05639 0.05268 -0.0199 1.0000 0.0481
-5.000 -0.3881 0.04858 0.04426 -0.0243 0.9960 0.0538
-4.750 -0.3623 0.04593 0.04163 -0.0262 0.9924 0.0555
-4.500 -0.3294 0.04353 0.03907 -0.0289 0.9873 0.0602
-4.250 -0.2937 0.04014 0.03522 -0.0318 0.9813 0.0661
-4.000 -0.2622 0.03775 0.03283 -0.0341 0.9759 0.0693
-3.750 -0.1869 0.02011 0.01517 -0.0418 0.9616 0.0810
-3.500 -0.1660 0.01861 0.01361 -0.0414 0.9548 0.0863
-3.250 -0.1342 0.01623 0.01099 -0.0430 0.9508 0.0970
-3.000 -0.1452 0.03009 0.02439 -0.0381 0.9561 0.0986
-2.750 -0.1129 0.02851 0.02264 -0.0395 0.9516 0.1129
-2.500 -0.0815 0.02717 0.02123 -0.0408 0.9472 0.1307
-2.250 -0.0559 0.02604 0.01997 -0.0410 0.9405 0.1583
-1.250 0.1050 0.02003 0.01263 -0.0450 0.9230 0.0887
-1.000 0.1382 0.01892 0.01130 -0.0449 0.9164 0.0737
-0.750 0.1775 0.01784 0.01015 -0.0466 0.9118 0.0710
-0.500 0.2242 0.01691 0.00909 -0.0494 0.9088 0.0656
-0.250 0.2617 0.01629 0.00847 -0.0507 0.9017 0.0639
0.000 0.3076 0.01507 0.00734 -0.0536 0.8964 0.0630
0.250 0.3625 0.01399 0.00635 -0.0586 0.8930 0.0632
0.500 0.3959 0.01344 0.00583 -0.0592 0.8823 0.0639
0.750 0.4388 0.01275 0.00517 -0.0617 0.8736 0.0685
1.000 0.4811 0.01226 0.00465 -0.0641 0.8618 0.0741
1.250 0.5111 0.01195 0.00435 -0.0639 0.8463 0.0827
1.500 0.6613 0.00964 0.00432 -0.0909 0.8315 1.0000
1.750 0.6823 0.00961 0.00423 -0.0890 0.8060 1.0000
2.000 0.7068 0.00956 0.00408 -0.0877 0.7748 1.0000
2.250 0.7329 0.00955 0.00390 -0.0868 0.7327 1.0000
2.500 0.7573 0.00970 0.00380 -0.0856 0.6822 1.0000
2.750 0.7774 0.01002 0.00382 -0.0836 0.6298 1.0000
3.000 0.7952 0.01042 0.00394 -0.0813 0.5833 1.0000
3.250 0.8126 0.01084 0.00413 -0.0790 0.5445 1.0000
3.500 0.8302 0.01127 0.00438 -0.0768 0.5106 1.0000
3.750 0.8478 0.01169 0.00463 -0.0746 0.4780 1.0000
4.000 0.8652 0.01209 0.00489 -0.0724 0.4455 1.0000
4.250 0.8820 0.01250 0.00517 -0.0701 0.4099 1.0000
4.500 0.8975 0.01298 0.00546 -0.0676 0.3709 1.0000
4.750 0.9133 0.01349 0.00578 -0.0653 0.3335 1.0000
5.000 0.9299 0.01402 0.00614 -0.0631 0.3031 1.0000
5.250 0.9475 0.01454 0.00653 -0.0612 0.2794 1.0000
5.500 0.9656 0.01506 0.00695 -0.0594 0.2617 1.0000
5.750 0.9847 0.01555 0.00738 -0.0578 0.2471 1.0000
6.000 1.0043 0.01600 0.00782 -0.0563 0.2342 1.0000
6.250 1.0240 0.01646 0.00828 -0.0548 0.2223 1.0000
6.500 1.0432 0.01696 0.00879 -0.0533 0.2114 1.0000
6.750 1.0616 0.01751 0.00929 -0.0517 0.2001 1.0000
7.000 1.0792 0.01806 0.00980 -0.0500 0.1873 1.0000
7.250 1.0964 0.01852 0.01028 -0.0482 0.1733 1.0000
7.500 1.1134 0.01897 0.01076 -0.0463 0.1592 1.0000
7.750 1.1303 0.01941 0.01127 -0.0445 0.1452 1.0000
8.000 1.1470 0.01986 0.01176 -0.0426 0.1307 1.0000
8.250 1.1630 0.02034 0.01223 -0.0407 0.1149 1.0000
8.500 1.1788 0.02091 0.01281 -0.0387 0.0979 1.0000
8.750 1.1898 0.02174 0.01359 -0.0360 0.0824 1.0000
9.000 1.1970 0.02284 0.01464 -0.0326 0.0692 1.0000
9.250 1.2029 0.02407 0.01587 -0.0291 0.0588 1.0000
9.500 1.2077 0.02543 0.01723 -0.0255 0.0525 1.0000
9.750 1.2159 0.02652 0.01837 -0.0227 0.0473 1.0000
10.000 1.2212 0.02801 0.01988 -0.0195 0.0438 1.0000
10.250 1.2306 0.02919 0.02120 -0.0170 0.0408 1.0000
10.500 1.2387 0.03048 0.02254 -0.0145 0.0387 1.0000
10.750 1.2454 0.03252 0.02456 -0.0121 0.0368 1.0000
11.000 1.2553 0.03405 0.02626 -0.0100 0.0355 1.0000
11.250 1.2638 0.03550 0.02788 -0.0079 0.0341 1.0000
11.500 1.2715 0.03712 0.02964 -0.0058 0.0328 1.0000
11.750 1.2774 0.03861 0.03122 -0.0038 0.0314 1.0000
12.000 1.2844 0.04049 0.03318 -0.0020 0.0306 1.0000
12.250 1.2922 0.04338 0.03617 -0.0005 0.0297 1.0000
12.500 1.2923 0.04610 0.03914 0.0016 0.0292 1.0000
12.750 1.2885 0.04859 0.04190 0.0038 0.0288 1.0000
13.000 1.2834 0.05141 0.04497 0.0057 0.0286 1.0000
13.250 1.2744 0.05454 0.04836 0.0073 0.0283 1.0000
13.500 1.2633 0.05800 0.05208 0.0085 0.0281 1.0000
13.750 1.2504 0.06188 0.05620 0.0090 0.0279 1.0000
14.000 1.2351 0.06615 0.06070 0.0088 0.0276 1.0000
14.250 1.2174 0.07121 0.06600 0.0078 0.0276 1.0000
14.500 1.1969 0.07715 0.07217 0.0059 0.0279 1.0000
14.750 1.1750 0.08371 0.07895 0.0030 0.0279 1.0000
15.000 1.1511 0.09118 0.08662 -0.0010 0.0280 1.0000
15.250 1.1272 0.09923 0.09485 -0.0055 0.0283 1.0000
15.500 1.0985 0.10892 0.10472 -0.0112 0.0287 1.0000
15.750 1.0698 0.11920 0.11514 -0.0172 0.0291 1.0000
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Polar data table (+)
Polar graphs
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