Fage & Collins 2 (fg2-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 2 (fg2-il) Reynolds number: 200,000 Max Cl/Cd: 69.12 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg2-il-200000-n5.txt Download as CSV file: xf-fg2-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 2
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4010 0.09300 0.08963 -0.0227 1.0000 0.0214
-8.000 -0.4095 0.09017 0.08687 -0.0235 1.0000 0.0215
-7.750 -0.4117 0.08707 0.08381 -0.0238 1.0000 0.0215
-7.500 -0.4113 0.08351 0.08028 -0.0250 1.0000 0.0215
-7.250 -0.4104 0.07984 0.07662 -0.0259 1.0000 0.0215
-6.750 -0.4070 0.07286 0.06963 -0.0259 1.0000 0.0213
-6.500 -0.4095 0.06972 0.06654 -0.0232 1.0000 0.0188
-6.250 -0.4082 0.06495 0.06172 -0.0244 1.0000 0.0171
-6.000 -0.3870 0.05721 0.05377 -0.0305 0.9967 0.0162
-5.750 -0.3633 0.05551 0.05204 -0.0326 0.9933 0.0178
-5.500 -0.3337 0.05098 0.04731 -0.0367 0.9884 0.0199
-5.250 -0.3075 0.04604 0.04214 -0.0396 0.9827 0.0197
-5.000 -0.2789 0.04126 0.03706 -0.0420 0.9776 0.0198
-4.500 -0.2302 0.03417 0.02937 -0.0429 0.9623 0.0236
-4.250 -0.2019 0.03138 0.02628 -0.0437 0.9552 0.0248
-4.000 -0.1779 0.02845 0.02300 -0.0429 0.9448 0.0255
-3.750 -0.1507 0.02610 0.02018 -0.0421 0.9344 0.0283
-3.500 -0.1207 0.02413 0.01764 -0.0417 0.9254 0.0298
-3.250 -0.0913 0.02141 0.01466 -0.0423 0.9158 0.0310
-3.000 -0.0580 0.02020 0.01334 -0.0437 0.9046 0.0337
-2.750 -0.0206 0.01863 0.01145 -0.0452 0.8942 0.0350
-2.500 0.0209 0.01721 0.00972 -0.0477 0.8841 0.0356
-2.250 0.0634 0.01628 0.00853 -0.0506 0.8709 0.0375
-2.000 0.1050 0.01536 0.00740 -0.0532 0.8528 0.0380
-1.750 0.1479 0.01446 0.00633 -0.0563 0.8279 0.0381
-1.500 0.1874 0.01377 0.00547 -0.0585 0.7937 0.0384
-1.000 0.2514 0.01301 0.00430 -0.0599 0.7168 0.0392
-0.750 0.2754 0.01264 0.00379 -0.0590 0.6855 0.0405
-0.500 0.2979 0.01240 0.00342 -0.0578 0.6587 0.0425
-0.250 0.3207 0.01230 0.00318 -0.0566 0.6359 0.0431
0.000 0.3437 0.01224 0.00299 -0.0554 0.6153 0.0433
0.250 0.3671 0.01222 0.00284 -0.0544 0.5973 0.0435
0.500 0.3907 0.01222 0.00273 -0.0534 0.5811 0.0437
0.750 0.4144 0.01223 0.00264 -0.0525 0.5659 0.0444
1.000 0.4383 0.01227 0.00258 -0.0516 0.5512 0.0453
1.250 0.4622 0.01232 0.00254 -0.0507 0.5367 0.0468
1.500 0.4860 0.01237 0.00254 -0.0497 0.5219 0.0494
1.750 0.5096 0.01243 0.00257 -0.0488 0.5071 0.0587
2.250 0.6716 0.01102 0.00311 -0.0737 0.4491 1.0000
2.500 0.6941 0.01121 0.00321 -0.0726 0.4322 1.0000
2.750 0.7166 0.01142 0.00333 -0.0715 0.4163 1.0000
3.000 0.7391 0.01162 0.00347 -0.0705 0.4018 1.0000
3.250 0.7619 0.01183 0.00362 -0.0695 0.3891 1.0000
3.500 0.7848 0.01204 0.00379 -0.0685 0.3785 1.0000
3.750 0.8075 0.01227 0.00400 -0.0675 0.3687 1.0000
4.000 0.8301 0.01250 0.00421 -0.0665 0.3582 1.0000
4.250 0.8531 0.01272 0.00444 -0.0656 0.3490 1.0000
4.500 0.8756 0.01298 0.00470 -0.0646 0.3411 1.0000
4.750 0.8987 0.01320 0.00497 -0.0637 0.3328 1.0000
5.000 0.9212 0.01346 0.00524 -0.0627 0.3242 1.0000
5.250 0.9436 0.01372 0.00553 -0.0616 0.3146 1.0000
5.750 0.9864 0.01427 0.00613 -0.0593 0.2800 1.0000
6.000 1.0068 0.01460 0.00641 -0.0580 0.2504 1.0000
6.250 1.0236 0.01520 0.00674 -0.0562 0.1945 1.0000
6.500 1.0395 0.01597 0.00729 -0.0543 0.1582 1.0000
6.750 1.0552 0.01679 0.00796 -0.0523 0.1283 1.0000
7.000 1.0728 0.01743 0.00855 -0.0507 0.1039 1.0000
7.250 1.0791 0.01901 0.00963 -0.0473 0.0298 1.0000
7.500 1.0924 0.01997 0.01056 -0.0448 0.0209 1.0000
7.750 1.1064 0.02088 0.01156 -0.0424 0.0168 1.0000
8.000 1.1209 0.02172 0.01259 -0.0401 0.0154 1.0000
8.250 1.1354 0.02252 0.01359 -0.0379 0.0147 1.0000
8.500 1.1481 0.02341 0.01466 -0.0354 0.0137 1.0000
8.750 1.1592 0.02436 0.01576 -0.0328 0.0126 1.0000
9.000 1.1681 0.02540 0.01695 -0.0298 0.0120 1.0000
9.250 1.1721 0.02651 0.01820 -0.0261 0.0113 1.0000
9.500 1.1730 0.02774 0.01955 -0.0221 0.0109 1.0000
9.750 1.1721 0.02916 0.02109 -0.0181 0.0106 1.0000
10.000 1.1710 0.03071 0.02275 -0.0144 0.0104 1.0000
10.250 1.1667 0.03265 0.02480 -0.0108 0.0101 1.0000
10.500 1.1648 0.03464 0.02690 -0.0079 0.0099 1.0000
10.750 1.1601 0.03725 0.02961 -0.0051 0.0096 1.0000
11.000 1.1639 0.03909 0.03160 -0.0033 0.0094 1.0000
11.250 1.1672 0.04109 0.03373 -0.0017 0.0094 1.0000
11.500 1.1706 0.04306 0.03587 -0.0005 0.0090 1.0000
11.750 1.1728 0.04524 0.03821 0.0004 0.0086 1.0000
12.000 1.1740 0.04784 0.04095 0.0014 0.0086 1.0000
12.250 1.1740 0.05041 0.04369 0.0017 0.0080 1.0000
12.500 1.1730 0.05337 0.04681 0.0020 0.0078 1.0000
12.750 1.1713 0.05652 0.05012 0.0021 0.0078 1.0000
13.000 1.1679 0.05999 0.05377 0.0019 0.0076 1.0000
13.250 1.1633 0.06372 0.05767 0.0014 0.0075 1.0000
13.500 1.1570 0.06780 0.06193 0.0005 0.0074 1.0000
13.750 1.1499 0.07208 0.06636 -0.0007 0.0073 1.0000
14.000 1.1406 0.07684 0.07132 -0.0022 0.0073 1.0000
14.250 1.1315 0.08164 0.07629 -0.0040 0.0073 1.0000
14.500 1.1212 0.08686 0.08166 -0.0061 0.0072 1.0000
14.750 1.1074 0.09294 0.08795 -0.0088 0.0074 1.0000
15.000 1.0955 0.09884 0.09400 -0.0117 0.0073 1.0000
15.250 1.0802 0.10581 0.10117 -0.0152 0.0074 1.0000
15.500 1.0664 0.11265 0.10816 -0.0188 0.0073 1.0000
15.750 1.0510 0.12021 0.11589 -0.0229 0.0074 1.0000
16.000 1.0346 0.12840 0.12424 -0.0274 0.0076 1.0000
16.250 1.0205 0.13632 0.13229 -0.0318 0.0075 1.0000
16.500 1.0032 0.14561 0.14171 -0.0370 0.0076 1.0000
16.750 0.9852 0.15578 0.15201 -0.0426 0.0078 1.0000
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Polar data table (+)
Polar graphs
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