Fage & Collins 1 (fg1-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 1 (fg1-il) Reynolds number: 100,000 Max Cl/Cd: 57.18 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg1-il-100000.txt Download as CSV file: xf-fg1-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4269 0.10211 0.09705 -0.0298 1.0000 0.0769
-8.750 -0.4451 0.10075 0.09580 -0.0313 1.0000 0.0772
-8.500 -0.4576 0.09884 0.09392 -0.0339 1.0000 0.0775
-8.250 -0.4276 0.09187 0.08698 -0.0261 1.0000 0.0804
-8.000 -0.4272 0.08930 0.08446 -0.0242 1.0000 0.0824
-7.750 -0.4312 0.08683 0.08205 -0.0233 1.0000 0.0844
-7.500 -0.4368 0.08436 0.07963 -0.0229 1.0000 0.0866
-7.250 -0.4436 0.08195 0.07725 -0.0233 1.0000 0.0890
-7.000 -0.4567 0.08088 0.07598 -0.0286 1.0000 0.0919
-6.750 -0.4561 0.07625 0.07141 -0.0273 1.0000 0.0931
-6.500 -0.4504 0.07287 0.06816 -0.0234 1.0000 0.0950
-6.250 -0.4461 0.07035 0.06566 -0.0212 1.0000 0.0980
-6.000 -0.4412 0.06775 0.06302 -0.0209 1.0000 0.1026
-5.750 -0.4356 0.06458 0.05957 -0.0238 1.0000 0.1089
-5.500 -0.4293 0.06171 0.05683 -0.0207 1.0000 0.1125
-5.250 -0.4177 0.06007 0.05475 -0.0228 1.0000 0.1239
-5.000 -0.4105 0.05624 0.05115 -0.0202 1.0000 0.1267
-4.750 -0.3994 0.05406 0.04893 -0.0189 1.0000 0.1342
-4.500 -0.3879 0.05127 0.04601 -0.0186 1.0000 0.1431
-4.250 -0.3743 0.04927 0.04379 -0.0184 1.0000 0.1568
-4.000 -0.3624 0.04699 0.04158 -0.0165 1.0000 0.1656
-3.750 -0.3494 0.04481 0.03933 -0.0154 1.0000 0.1796
-3.500 -0.3356 0.04321 0.03753 -0.0147 1.0000 0.2044
-3.250 -0.3234 0.04104 0.03544 -0.0129 1.0000 0.2227
-3.000 -0.3121 0.03945 0.03386 -0.0109 1.0000 0.2541
-2.750 -0.3020 0.03785 0.03235 -0.0084 1.0000 0.2882
-2.500 -0.2929 0.03647 0.03103 -0.0055 1.0000 0.3327
-2.250 -0.2822 0.03559 0.03016 -0.0027 1.0000 0.3776
-2.000 -0.2755 0.03332 0.02813 0.0015 1.0000 0.4146
-1.750 -0.2647 0.03209 0.02695 0.0046 1.0000 0.4556
-1.500 -0.2449 0.03029 0.02524 0.0063 0.9967 0.4937
-1.250 -0.1129 0.02823 0.01983 -0.0110 0.9891 0.1370
-1.000 -0.0668 0.02684 0.01808 -0.0136 0.9807 0.1171
-0.750 -0.0196 0.02646 0.01724 -0.0163 0.9714 0.1066
-0.500 0.0255 0.02520 0.01591 -0.0193 0.9625 0.1004
-0.250 0.0685 0.02453 0.01504 -0.0216 0.9519 0.0950
0.000 0.1119 0.02422 0.01464 -0.0242 0.9409 0.0925
0.250 0.1559 0.02353 0.01400 -0.0271 0.9305 0.0921
0.500 0.2052 0.02265 0.01329 -0.0309 0.9221 0.0946
0.750 0.2452 0.02213 0.01284 -0.0330 0.9094 0.0993
1.000 0.2897 0.02170 0.01238 -0.0357 0.8969 0.1047
1.250 0.3408 0.02112 0.01183 -0.0396 0.8845 0.1161
1.500 0.4894 0.01791 0.01080 -0.0632 0.8827 1.0000
1.750 0.5471 0.01706 0.00986 -0.0676 0.8681 1.0000
2.000 0.6011 0.01631 0.00908 -0.0716 0.8518 1.0000
2.250 0.6479 0.01565 0.00843 -0.0742 0.8331 1.0000
2.500 0.6808 0.01523 0.00802 -0.0741 0.8078 1.0000
2.750 0.7150 0.01481 0.00760 -0.0743 0.7790 1.0000
3.000 0.7499 0.01445 0.00719 -0.0747 0.7439 1.0000
3.250 0.7836 0.01426 0.00687 -0.0748 0.7008 1.0000
3.500 0.8133 0.01434 0.00673 -0.0743 0.6528 1.0000
3.750 0.8383 0.01466 0.00680 -0.0732 0.6052 1.0000
4.000 0.8601 0.01515 0.00703 -0.0715 0.5611 1.0000
4.250 0.8798 0.01576 0.00738 -0.0696 0.5190 1.0000
4.500 0.8980 0.01644 0.00782 -0.0674 0.4781 1.0000
4.750 0.9145 0.01712 0.00830 -0.0650 0.4376 1.0000
5.000 0.9314 0.01782 0.00878 -0.0628 0.4017 1.0000
5.250 0.9486 0.01852 0.00928 -0.0606 0.3702 1.0000
5.500 0.9668 0.01920 0.00987 -0.0588 0.3438 1.0000
5.750 0.9864 0.01992 0.01043 -0.0573 0.3230 1.0000
6.000 1.0062 0.02061 0.01109 -0.0558 0.3042 1.0000
6.250 1.0259 0.02129 0.01176 -0.0543 0.2873 1.0000
6.500 1.0457 0.02199 0.01246 -0.0529 0.2716 1.0000
6.750 1.0650 0.02272 0.01322 -0.0514 0.2560 1.0000
7.000 1.0836 0.02348 0.01399 -0.0498 0.2403 1.0000
7.250 1.1012 0.02427 0.01479 -0.0480 0.2237 1.0000
7.500 1.1181 0.02514 0.01565 -0.0462 0.2069 1.0000
7.750 1.1341 0.02609 0.01654 -0.0443 0.1894 1.0000
8.000 1.1488 0.02713 0.01750 -0.0424 0.1718 1.0000
8.250 1.1593 0.02795 0.01843 -0.0395 0.1549 1.0000
8.500 1.1699 0.02883 0.01939 -0.0367 0.1391 1.0000
8.750 1.1790 0.02965 0.02030 -0.0337 0.1242 1.0000
9.000 1.1872 0.03052 0.02125 -0.0305 0.1101 1.0000
9.250 1.1950 0.03162 0.02236 -0.0274 0.0973 1.0000
9.500 1.2060 0.03321 0.02392 -0.0250 0.0871 1.0000
9.750 1.2181 0.03491 0.02554 -0.0230 0.0782 1.0000
10.000 1.2288 0.03691 0.02784 -0.0205 0.0718 1.0000
10.250 1.2462 0.03918 0.03004 -0.0195 0.0667 1.0000
10.500 1.2572 0.04198 0.03319 -0.0175 0.0637 1.0000
10.750 1.2612 0.04413 0.03567 -0.0143 0.0608 1.0000
11.000 1.2645 0.04613 0.03786 -0.0113 0.0583 1.0000
11.250 1.2740 0.04860 0.04037 -0.0097 0.0560 1.0000
11.500 1.2779 0.05291 0.04488 -0.0079 0.0547 1.0000
11.750 1.2651 0.05547 0.04780 -0.0034 0.0544 1.0000
12.000 1.2512 0.05841 0.05106 0.0004 0.0542 1.0000
12.250 1.2334 0.06169 0.05464 0.0037 0.0541 1.0000
12.500 1.2135 0.06538 0.05861 0.0062 0.0540 1.0000
12.750 1.1912 0.06956 0.06306 0.0078 0.0540 1.0000
13.000 1.1695 0.07421 0.06793 0.0083 0.0542 1.0000
13.250 1.1446 0.07958 0.07351 0.0077 0.0543 1.0000
13.500 1.1206 0.08562 0.07972 0.0060 0.0546 1.0000
13.750 1.0940 0.09229 0.08660 0.0028 0.0550 1.0000
14.000 0.7138 0.14146 0.13628 -0.0240 0.0885 1.0000
14.250 0.7120 0.14577 0.14060 -0.0252 0.0891 1.0000
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Polar data table (+)
Polar graphs
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