Fage & Collins 1 (fg1-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 1 (fg1-il) Reynolds number: 200,000 Max Cl/Cd: 66.01 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg1-il-200000-n5.txt Download as CSV file: xf-fg1-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4138 0.09001 0.08640 -0.0270 1.0000 0.0299
-8.500 -0.4194 0.08761 0.08405 -0.0262 1.0000 0.0303
-8.250 -0.4308 0.08554 0.08205 -0.0248 1.0000 0.0305
-8.000 -0.4444 0.08356 0.08015 -0.0229 1.0000 0.0308
-7.750 -0.4445 0.08034 0.07694 -0.0244 0.9987 0.0313
-7.500 -0.4242 0.07515 0.07168 -0.0320 0.9940 0.0326
-7.250 -0.3931 0.06618 0.06230 -0.0484 0.9857 0.0345
-7.000 -0.3824 0.06249 0.05868 -0.0482 0.9820 0.0349
-6.750 -0.3660 0.05951 0.05568 -0.0492 0.9782 0.0355
-6.500 -0.3455 0.05632 0.05241 -0.0514 0.9750 0.0363
-6.250 -0.3290 0.05325 0.04925 -0.0525 0.9693 0.0373
-6.000 -0.2961 0.04910 0.04450 -0.0568 0.9647 0.0417
-5.750 -0.2837 0.04511 0.04036 -0.0565 0.9585 0.0424
-5.500 -0.2639 0.04251 0.03783 -0.0573 0.9554 0.0435
-5.250 -0.2392 0.04017 0.03539 -0.0584 0.9530 0.0449
-5.000 -0.2214 0.03806 0.03313 -0.0577 0.9472 0.0466
-4.750 -0.1956 0.03528 0.02980 -0.0578 0.9430 0.0519
-4.500 -0.1698 0.03300 0.02752 -0.0588 0.9408 0.0533
-4.250 -0.1477 0.03136 0.02577 -0.0584 0.9354 0.0554
-4.000 -0.1198 0.02958 0.02360 -0.0585 0.9305 0.0632
-3.500 -0.0574 0.02422 0.01735 -0.0579 0.9224 0.0411
-3.250 -0.0287 0.02225 0.01524 -0.0581 0.9174 0.0393
-3.000 0.0057 0.02052 0.01323 -0.0591 0.9143 0.0375
-2.750 0.0430 0.01905 0.01146 -0.0606 0.9120 0.0364
-2.500 0.0691 0.01817 0.01041 -0.0599 0.9058 0.0364
-2.250 0.1039 0.01732 0.00947 -0.0613 0.9017 0.0376
-2.000 0.1442 0.01637 0.00838 -0.0636 0.8985 0.0376
-1.750 0.1761 0.01562 0.00753 -0.0642 0.8925 0.0371
-1.500 0.2094 0.01496 0.00679 -0.0650 0.8863 0.0367
-1.250 0.2494 0.01426 0.00606 -0.0674 0.8818 0.0367
-1.000 0.2734 0.01384 0.00565 -0.0664 0.8721 0.0368
-0.750 0.3056 0.01334 0.00515 -0.0670 0.8626 0.0370
-0.500 0.3362 0.01290 0.00473 -0.0674 0.8518 0.0375
-0.250 0.3601 0.01257 0.00442 -0.0663 0.8378 0.0380
0.000 0.3842 0.01231 0.00417 -0.0653 0.8232 0.0393
0.250 0.4090 0.01206 0.00392 -0.0643 0.8065 0.0407
0.500 0.4334 0.01185 0.00369 -0.0634 0.7880 0.0414
0.750 0.4605 0.01166 0.00342 -0.0629 0.7621 0.0418
1.000 0.4890 0.01151 0.00312 -0.0626 0.7257 0.0427
1.250 0.5156 0.01150 0.00288 -0.0620 0.6796 0.0438
1.500 0.5385 0.01162 0.00277 -0.0607 0.6314 0.0454
1.750 0.5592 0.01182 0.00276 -0.0590 0.5898 0.0475
2.250 0.7066 0.01075 0.00345 -0.0804 0.4954 1.0000
2.500 0.7266 0.01103 0.00359 -0.0787 0.4704 1.0000
2.750 0.7463 0.01133 0.00375 -0.0769 0.4455 1.0000
3.000 0.7662 0.01161 0.00392 -0.0753 0.4203 1.0000
3.250 0.7861 0.01191 0.00411 -0.0737 0.3964 1.0000
3.500 0.8060 0.01221 0.00430 -0.0721 0.3729 1.0000
3.750 0.8257 0.01253 0.00452 -0.0704 0.3499 1.0000
4.000 0.8454 0.01286 0.00477 -0.0688 0.3263 1.0000
4.250 0.8645 0.01323 0.00503 -0.0671 0.3009 1.0000
4.500 0.8831 0.01365 0.00531 -0.0654 0.2731 1.0000
4.750 0.9015 0.01409 0.00561 -0.0636 0.2461 1.0000
5.000 0.9206 0.01450 0.00594 -0.0620 0.2261 1.0000
5.250 0.9401 0.01490 0.00628 -0.0605 0.2120 1.0000
5.750 0.9796 0.01568 0.00703 -0.0575 0.1911 1.0000
6.000 0.9989 0.01609 0.00743 -0.0560 0.1827 1.0000
6.250 1.0187 0.01648 0.00784 -0.0546 0.1750 1.0000
6.500 1.0378 0.01691 0.00828 -0.0531 0.1679 1.0000
6.750 1.0575 0.01730 0.00874 -0.0517 0.1599 1.0000
7.000 1.0762 0.01775 0.00921 -0.0501 0.1523 1.0000
7.250 1.0954 0.01814 0.00965 -0.0486 0.1422 1.0000
7.500 1.1146 0.01853 0.01006 -0.0472 0.1287 1.0000
7.750 1.1329 0.01898 0.01049 -0.0457 0.1126 1.0000
8.000 1.1501 0.01950 0.01097 -0.0440 0.0964 1.0000
8.250 1.1660 0.02013 0.01155 -0.0421 0.0840 1.0000
8.750 1.1947 0.02149 0.01292 -0.0379 0.0648 1.0000
9.000 1.2080 0.02218 0.01365 -0.0355 0.0570 1.0000
9.250 1.2199 0.02296 0.01445 -0.0331 0.0494 1.0000
9.500 1.2313 0.02379 0.01529 -0.0306 0.0414 1.0000
9.750 1.2427 0.02462 0.01618 -0.0282 0.0353 1.0000
10.000 1.2525 0.02555 0.01718 -0.0256 0.0304 1.0000
10.250 1.2612 0.02658 0.01825 -0.0229 0.0272 1.0000
10.500 1.2687 0.02767 0.01943 -0.0202 0.0250 1.0000
10.750 1.2761 0.02876 0.02065 -0.0176 0.0232 1.0000
11.000 1.2824 0.02996 0.02193 -0.0151 0.0218 1.0000
11.250 1.2844 0.03147 0.02351 -0.0123 0.0206 1.0000
11.500 1.2892 0.03283 0.02504 -0.0100 0.0198 1.0000
11.750 1.2933 0.03430 0.02665 -0.0078 0.0186 1.0000
12.000 1.2953 0.03599 0.02848 -0.0056 0.0181 1.0000
12.250 1.2952 0.03791 0.03053 -0.0036 0.0173 1.0000
12.500 1.2941 0.04002 0.03276 -0.0019 0.0169 1.0000
12.750 1.2906 0.04246 0.03533 -0.0003 0.0166 1.0000
13.000 1.2851 0.04525 0.03824 0.0009 0.0162 1.0000
13.250 1.2779 0.04842 0.04154 0.0018 0.0159 1.0000
13.500 1.2745 0.05141 0.04470 0.0021 0.0157 1.0000
13.750 1.2691 0.05480 0.04826 0.0021 0.0155 1.0000
14.000 1.2632 0.05848 0.05211 0.0017 0.0152 1.0000
14.250 1.2561 0.06255 0.05636 0.0007 0.0148 1.0000
14.500 1.2481 0.06697 0.06095 -0.0006 0.0145 1.0000
14.750 1.2391 0.07173 0.06587 -0.0022 0.0144 1.0000
15.000 1.2295 0.07672 0.07102 -0.0041 0.0143 1.0000
15.250 1.2180 0.08224 0.07670 -0.0064 0.0140 1.0000
15.500 1.2068 0.08778 0.08239 -0.0087 0.0141 1.0000
15.750 1.1938 0.09394 0.08870 -0.0117 0.0137 1.0000
16.000 1.1801 0.10036 0.09525 -0.0148 0.0134 1.0000
16.250 1.1668 0.10673 0.10177 -0.0177 0.0135 1.0000
16.500 1.1534 0.11337 0.10855 -0.0210 0.0134 1.0000
16.750 1.1393 0.12030 0.11561 -0.0245 0.0133 1.0000
17.000 1.1251 0.12749 0.12293 -0.0281 0.0133 1.0000
17.250 1.1096 0.13518 0.13077 -0.0321 0.0133 1.0000
17.500 1.0933 0.14339 0.13912 -0.0365 0.0133 1.0000
17.750 1.0715 0.15334 0.14924 -0.0419 0.0135 1.0000
18.000 1.0431 0.16588 0.16194 -0.0487 0.0136 1.0000
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Polar data table (+)
Polar graphs
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