Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Fage & Collins 4 (fg4-il) Reynolds number: 200,000 Max Cl/Cd: 46.96 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fg4-il-200000-n5.txt Download as CSV file: xf-fg4-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 4
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2159 0.09074 0.08706 -0.0619 0.9670 0.0376
-8.750 -0.2171 0.08692 0.08325 -0.0657 0.9585 0.0377
-8.250 -0.1995 0.08073 0.07711 -0.0665 0.9464 0.0381
-8.000 -0.1866 0.07776 0.07415 -0.0677 0.9420 0.0384
-7.750 -0.1829 0.07496 0.07135 -0.0684 0.9338 0.0388
-7.500 -0.1678 0.07141 0.06778 -0.0715 0.9295 0.0396
-7.250 -0.1584 0.06795 0.06429 -0.0736 0.9216 0.0407
-7.000 -0.1412 0.06335 0.05959 -0.0786 0.9169 0.0422
-6.750 -0.1334 0.05725 0.05303 -0.0839 0.9072 0.0434
-6.500 -0.1125 0.05341 0.04914 -0.0858 0.9033 0.0437
-6.250 -0.0857 0.05031 0.04605 -0.0880 0.9007 0.0441
-6.000 -0.0719 0.04816 0.04386 -0.0873 0.8920 0.0447
-5.750 -0.0452 0.04538 0.04098 -0.0894 0.8872 0.0456
-5.500 -0.0246 0.04284 0.03830 -0.0898 0.8793 0.0468
-5.000 0.0091 0.03736 0.03214 -0.0878 0.8594 0.0506
-4.750 0.0365 0.03511 0.02985 -0.0890 0.8517 0.0513
-4.500 0.0467 0.03373 0.02841 -0.0860 0.8377 0.0520
-4.000 0.0707 0.03101 0.02513 -0.0795 0.8062 0.0585
-3.500 0.1130 0.02491 0.01819 -0.0751 0.7750 0.0372
-3.250 0.1445 0.02337 0.01642 -0.0759 0.7561 0.0366
-3.000 0.1778 0.02191 0.01461 -0.0767 0.7345 0.0361
-2.750 0.2090 0.02075 0.01310 -0.0771 0.7141 0.0357
-2.500 0.2365 0.01978 0.01181 -0.0766 0.6959 0.0356
-2.250 0.2618 0.01900 0.01077 -0.0758 0.6804 0.0355
-2.000 0.2865 0.01839 0.00992 -0.0748 0.6640 0.0359
-1.750 0.3093 0.01797 0.00924 -0.0733 0.6460 0.0368
-1.500 0.3318 0.01755 0.00861 -0.0719 0.6303 0.0372
-1.250 0.3518 0.01714 0.00801 -0.0699 0.6110 0.0373
-1.000 0.3718 0.01678 0.00751 -0.0680 0.5935 0.0374
-0.500 0.4113 0.01620 0.00670 -0.0641 0.5627 0.0376
-0.250 0.4316 0.01588 0.00633 -0.0623 0.5497 0.0379
0.000 0.4500 0.01561 0.00603 -0.0602 0.5351 0.0384
0.250 0.4678 0.01545 0.00581 -0.0579 0.5213 0.0388
0.500 0.4866 0.01528 0.00563 -0.0559 0.5091 0.0394
0.750 0.5040 0.01518 0.00549 -0.0536 0.4952 0.0401
1.000 0.5199 0.01514 0.00540 -0.0510 0.4787 0.0415
1.250 0.5360 0.01516 0.00534 -0.0484 0.4620 0.0432
1.500 0.5512 0.01515 0.00527 -0.0457 0.4428 0.0441
1.750 0.5652 0.01521 0.00523 -0.0428 0.4184 0.0451
2.000 0.5808 0.01532 0.00523 -0.0403 0.3978 0.0464
2.250 0.5945 0.01552 0.00527 -0.0374 0.3720 0.0474
2.500 0.6094 0.01573 0.00534 -0.0347 0.3495 0.0493
2.750 0.6246 0.01596 0.00545 -0.0322 0.3287 0.0515
3.000 0.6406 0.01621 0.00559 -0.0299 0.3098 0.0566
3.250 0.6556 0.01648 0.00578 -0.0275 0.2877 0.0711
3.750 0.8862 0.01887 0.00867 -0.0702 0.0690 1.0000
4.000 0.8999 0.01937 0.00908 -0.0677 0.0649 1.0000
4.250 0.9157 0.01976 0.00943 -0.0655 0.0632 1.0000
4.500 0.9315 0.02015 0.00981 -0.0633 0.0619 1.0000
4.750 0.9474 0.02055 0.01020 -0.0613 0.0610 1.0000
5.000 0.9633 0.02095 0.01061 -0.0592 0.0603 1.0000
5.250 0.9785 0.02140 0.01108 -0.0571 0.0596 1.0000
5.500 0.9936 0.02186 0.01155 -0.0550 0.0591 1.0000
5.750 1.0080 0.02237 0.01208 -0.0528 0.0585 1.0000
6.000 1.0218 0.02292 0.01265 -0.0506 0.0580 1.0000
6.250 1.0355 0.02349 0.01325 -0.0485 0.0577 1.0000
6.500 1.0481 0.02412 0.01391 -0.0462 0.0572 1.0000
6.750 1.0599 0.02481 0.01465 -0.0439 0.0569 1.0000
7.000 1.0712 0.02553 0.01541 -0.0417 0.0566 1.0000
7.250 1.0819 0.02631 0.01624 -0.0394 0.0563 1.0000
7.500 1.0929 0.02710 0.01707 -0.0373 0.0562 1.0000
7.750 1.1038 0.02790 0.01791 -0.0352 0.0561 1.0000
8.000 1.1134 0.02881 0.01888 -0.0331 0.0560 1.0000
8.250 1.1223 0.02979 0.01993 -0.0311 0.0558 1.0000
8.500 1.1312 0.03081 0.02100 -0.0291 0.0555 1.0000
8.750 1.1388 0.03195 0.02220 -0.0271 0.0553 1.0000
9.000 1.1458 0.03318 0.02348 -0.0252 0.0552 1.0000
9.250 1.1518 0.03451 0.02488 -0.0234 0.0550 1.0000
9.500 1.1576 0.03593 0.02636 -0.0217 0.0549 1.0000
9.750 1.1630 0.03744 0.02793 -0.0201 0.0547 1.0000
10.000 1.1679 0.03905 0.02961 -0.0187 0.0545 1.0000
10.250 1.1723 0.04078 0.03140 -0.0173 0.0542 1.0000
10.500 1.1770 0.04254 0.03322 -0.0162 0.0543 1.0000
10.750 1.1813 0.04443 0.03516 -0.0152 0.0541 1.0000
11.000 1.1858 0.04633 0.03713 -0.0143 0.0540 1.0000
11.250 1.1905 0.04825 0.03911 -0.0135 0.0540 1.0000
11.500 1.1946 0.05029 0.04119 -0.0127 0.0539 1.0000
11.750 1.2000 0.05223 0.04319 -0.0121 0.0537 1.0000
12.000 1.2049 0.05423 0.04524 -0.0116 0.0535 1.0000
12.250 1.2096 0.05628 0.04735 -0.0110 0.0532 1.0000
12.500 1.2145 0.05835 0.04946 -0.0106 0.0528 1.0000
12.750 1.2192 0.06043 0.05157 -0.0102 0.0522 1.0000
13.000 1.2246 0.06239 0.05352 -0.0097 0.0515 1.0000
13.250 1.2329 0.06397 0.05506 -0.0090 0.0510 1.0000
13.500 1.2424 0.06543 0.05651 -0.0083 0.0505 1.0000
13.750 1.2458 0.06785 0.05905 -0.0084 0.0502 1.0000
14.000 1.2492 0.07028 0.06160 -0.0085 0.0499 1.0000
14.250 1.2536 0.07260 0.06402 -0.0086 0.0495 1.0000
14.500 1.2568 0.07509 0.06662 -0.0088 0.0490 1.0000
14.750 1.2599 0.07763 0.06925 -0.0091 0.0486 1.0000
15.000 1.2639 0.08002 0.07174 -0.0093 0.0482 1.0000
15.250 1.2677 0.08245 0.07425 -0.0095 0.0477 1.0000
15.500 1.2710 0.08500 0.07688 -0.0098 0.0474 1.0000
15.750 1.2748 0.08746 0.07941 -0.0101 0.0470 1.0000
16.000 1.2781 0.08998 0.08198 -0.0105 0.0464 1.0000
16.250 1.2835 0.09213 0.08417 -0.0107 0.0459 1.0000
16.500 1.2918 0.09373 0.08573 -0.0106 0.0452 1.0000
16.750 1.2898 0.09725 0.08941 -0.0117 0.0450 1.0000
17.000 1.2864 0.10105 0.09338 -0.0130 0.0446 1.0000
17.250 1.2851 0.10452 0.09699 -0.0142 0.0442 1.0000
17.500 1.2847 0.10786 0.10046 -0.0153 0.0439 1.0000
17.750 1.2792 0.11217 0.10495 -0.0171 0.0431 1.0000
18.000 1.2773 0.11583 0.10873 -0.0185 0.0427 1.0000
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Polar data table (+)
Polar graphs
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