Fage & Collins 1 (fg1-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 1 (fg1-il) Reynolds number: 50,000 Max Cl/Cd: 37.48 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg1-il-50000-n5.txt Download as CSV file: xf-fg1-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4055 0.10367 0.09643 -0.0250 1.0000 0.1279
-8.750 -0.4153 0.10189 0.09476 -0.0255 1.0000 0.1325
-8.500 -0.4405 0.10126 0.09432 -0.0266 1.0000 0.1345
-8.250 -0.4262 0.09657 0.08966 -0.0243 1.0000 0.1384
-8.000 -0.4233 0.09382 0.08696 -0.0226 1.0000 0.1438
-7.750 -0.4396 0.09220 0.08546 -0.0241 1.0000 0.1496
-7.500 -0.4477 0.08939 0.08275 -0.0248 1.0000 0.1523
-7.250 -0.4365 0.08592 0.07931 -0.0214 1.0000 0.1568
-7.000 -0.4427 0.08375 0.07719 -0.0217 1.0000 0.1646
-6.750 -0.4458 0.08074 0.07423 -0.0213 1.0000 0.1698
-6.500 -0.4409 0.07802 0.07155 -0.0190 1.0000 0.1760
-6.250 -0.4445 0.07535 0.06889 -0.0193 1.0000 0.1861
-5.750 -0.4372 0.07011 0.06368 -0.0160 1.0000 0.2069
-5.500 -0.4343 0.06764 0.06123 -0.0143 1.0000 0.2239
-4.500 -0.3738 0.05374 0.04632 -0.0217 1.0000 0.1652
-4.250 -0.3375 0.04756 0.03911 -0.0235 1.0000 0.0861
-4.000 -0.3220 0.04497 0.03639 -0.0224 1.0000 0.0828
-3.750 -0.3040 0.04251 0.03360 -0.0214 1.0000 0.0789
-3.500 -0.2852 0.04043 0.03113 -0.0203 1.0000 0.0773
-3.250 -0.2662 0.03865 0.02901 -0.0192 1.0000 0.0769
-3.000 -0.2458 0.03706 0.02700 -0.0179 1.0000 0.0756
-2.750 -0.2245 0.03606 0.02547 -0.0164 1.0000 0.0736
-2.500 -0.2049 0.03448 0.02372 -0.0153 1.0000 0.0727
-2.250 -0.1806 0.03313 0.02215 -0.0149 0.9983 0.0720
-2.000 -0.1435 0.03186 0.02059 -0.0169 0.9915 0.0711
-1.750 -0.1060 0.03080 0.01926 -0.0188 0.9847 0.0705
-1.500 -0.0688 0.02987 0.01807 -0.0206 0.9771 0.0706
-1.250 -0.0318 0.02917 0.01713 -0.0224 0.9691 0.0721
-1.000 0.0066 0.02857 0.01632 -0.0243 0.9611 0.0736
-0.750 0.0485 0.02787 0.01551 -0.0269 0.9536 0.0743
-0.500 0.0878 0.02721 0.01478 -0.0291 0.9445 0.0751
-0.250 0.1276 0.02669 0.01419 -0.0314 0.9353 0.0765
0.000 0.1704 0.02627 0.01372 -0.0343 0.9263 0.0784
0.250 0.2070 0.02592 0.01332 -0.0360 0.9146 0.0814
0.500 0.2446 0.02565 0.01298 -0.0377 0.9027 0.0875
0.750 0.2840 0.02528 0.01267 -0.0399 0.8909 0.0963
1.000 0.3267 0.02484 0.01237 -0.0425 0.8797 0.1133
1.250 0.4093 0.02248 0.01231 -0.0537 0.8723 1.0000
1.500 0.4463 0.02241 0.01210 -0.0549 0.8574 1.0000
1.750 0.4826 0.02231 0.01190 -0.0560 0.8413 1.0000
2.000 0.5187 0.02215 0.01169 -0.0570 0.8239 1.0000
2.250 0.5526 0.02191 0.01144 -0.0573 0.8029 1.0000
2.500 0.5844 0.02156 0.01106 -0.0570 0.7769 1.0000
2.750 0.6155 0.02115 0.01062 -0.0564 0.7461 1.0000
3.000 0.6483 0.02081 0.01023 -0.0561 0.7123 1.0000
3.250 0.6805 0.02064 0.00999 -0.0560 0.6772 1.0000
3.500 0.7134 0.02058 0.00983 -0.0561 0.6420 1.0000
3.750 0.7454 0.02066 0.00977 -0.0560 0.6053 1.0000
4.000 0.7728 0.02095 0.00990 -0.0554 0.5687 1.0000
4.250 0.7977 0.02137 0.01015 -0.0544 0.5337 1.0000
4.500 0.8204 0.02189 0.01055 -0.0532 0.5005 1.0000
4.750 0.8416 0.02248 0.01104 -0.0517 0.4690 1.0000
5.000 0.8620 0.02311 0.01158 -0.0503 0.4393 1.0000
5.250 0.8819 0.02377 0.01219 -0.0487 0.4106 1.0000
5.500 0.9016 0.02447 0.01279 -0.0472 0.3841 1.0000
5.750 0.9217 0.02520 0.01352 -0.0459 0.3591 1.0000
6.000 0.9424 0.02597 0.01422 -0.0446 0.3376 1.0000
6.250 0.9624 0.02675 0.01503 -0.0434 0.3160 1.0000
6.500 0.9821 0.02755 0.01583 -0.0421 0.2965 1.0000
6.750 1.0010 0.02836 0.01664 -0.0407 0.2785 1.0000
7.000 1.0199 0.02919 0.01750 -0.0393 0.2621 1.0000
7.250 1.0384 0.03006 0.01844 -0.0379 0.2468 1.0000
7.500 1.0564 0.03098 0.01943 -0.0364 0.2322 1.0000
7.750 1.0735 0.03194 0.02048 -0.0349 0.2178 1.0000
8.000 1.0902 0.03298 0.02162 -0.0333 0.2041 1.0000
8.250 1.1059 0.03410 0.02288 -0.0316 0.1906 1.0000
8.500 1.1207 0.03532 0.02421 -0.0298 0.1774 1.0000
8.750 1.1349 0.03664 0.02563 -0.0280 0.1649 1.0000
9.000 1.1471 0.03795 0.02699 -0.0260 0.1527 1.0000
9.250 1.1568 0.03930 0.02849 -0.0237 0.1409 1.0000
9.500 1.1625 0.04068 0.03014 -0.0208 0.1291 1.0000
9.750 1.1655 0.04202 0.03164 -0.0177 0.1184 1.0000
10.000 1.1656 0.04320 0.03286 -0.0143 0.1093 1.0000
10.250 1.1650 0.04459 0.03437 -0.0112 0.1005 1.0000
10.500 1.1648 0.04643 0.03639 -0.0084 0.0922 1.0000
10.750 1.1635 0.04807 0.03795 -0.0058 0.0862 1.0000
11.000 1.1629 0.05066 0.04087 -0.0036 0.0797 1.0000
11.250 1.1610 0.05283 0.04303 -0.0017 0.0749 1.0000
11.500 1.1569 0.05580 0.04627 0.0000 0.0706 1.0000
11.750 1.1500 0.05901 0.04973 0.0014 0.0666 1.0000
12.000 1.1453 0.06206 0.05289 0.0025 0.0639 1.0000
12.250 1.1429 0.06509 0.05589 0.0033 0.0614 1.0000
12.500 1.1282 0.06982 0.06098 0.0033 0.0600 1.0000
12.750 1.1112 0.07512 0.06659 0.0025 0.0591 1.0000
13.000 1.0914 0.08121 0.07294 0.0006 0.0586 1.0000
13.250 1.0672 0.08856 0.08053 -0.0027 0.0583 1.0000
13.500 1.0409 0.09714 0.08931 -0.0070 0.0589 1.0000
13.750 1.0096 0.10764 0.09994 -0.0128 0.0598 1.0000
14.000 0.9765 0.11968 0.11206 -0.0195 0.0605 1.0000
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Polar data table (+)
Polar graphs
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