GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il) Reynolds number: 100,000 Max Cl/Cd: 67.6 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe804-il-100000-n5.txt Download as CSV file: xf-goe804-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 804 (EA 8) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2779 0.10598 0.10130 -0.0445 0.9709 0.0365
-6.750 -0.2714 0.10389 0.09923 -0.0470 0.9675 0.0375
-6.500 -0.2731 0.10249 0.09788 -0.0479 0.9613 0.0381
-6.250 -0.2576 0.09976 0.09517 -0.0545 0.9567 0.0385
-6.000 -0.2462 0.09703 0.09245 -0.0595 0.9507 0.0387
-5.750 -0.2252 0.09341 0.08881 -0.0665 0.9458 0.0388
-5.500 -0.2185 0.08848 0.08391 -0.0637 0.9439 0.0395
-5.250 -0.2037 0.08461 0.08003 -0.0638 0.9420 0.0408
-5.000 -0.1963 0.08182 0.07726 -0.0647 0.9358 0.0413
-4.750 -0.1752 0.07808 0.07350 -0.0692 0.9316 0.0422
-4.500 -0.1451 0.07386 0.06922 -0.0761 0.9286 0.0427
-4.250 -0.1190 0.06988 0.06519 -0.0820 0.9244 0.0427
-4.000 -0.0597 0.06181 0.05686 -0.0986 0.9203 0.0278
-3.750 -0.0113 0.05632 0.05118 -0.1088 0.9180 0.0280
-3.500 0.0384 0.05083 0.04547 -0.1185 0.9166 0.0279
-3.250 0.0936 0.04532 0.03967 -0.1288 0.9158 0.0274
-3.000 0.1665 0.03848 0.03227 -0.1426 0.9168 0.0288
-2.750 0.2143 0.03585 0.02931 -0.1489 0.9160 0.0317
-2.500 0.2821 0.03101 0.02354 -0.1588 0.9173 0.0365
-2.250 0.3319 0.02857 0.02043 -0.1641 0.9170 0.0424
-2.000 0.3743 0.02712 0.01846 -0.1674 0.9159 0.0522
-1.750 0.4122 0.02641 0.01747 -0.1698 0.9144 0.0648
-1.500 0.4492 0.02596 0.01685 -0.1719 0.9130 0.0784
-1.250 0.4726 0.02577 0.01646 -0.1713 0.9076 0.0874
-1.000 0.5026 0.02549 0.01612 -0.1721 0.9041 0.0975
-0.750 0.5360 0.02515 0.01565 -0.1733 0.9017 0.1046
-0.500 0.5712 0.02480 0.01531 -0.1751 0.8997 0.1122
-0.250 0.6077 0.02455 0.01505 -0.1770 0.8980 0.1249
0.000 0.6279 0.02467 0.01519 -0.1759 0.8912 0.1380
0.250 0.6601 0.02459 0.01515 -0.1770 0.8879 0.1607
0.500 0.6966 0.02437 0.01505 -0.1790 0.8854 0.2173
0.750 0.7136 0.02288 0.01521 -0.1766 0.8810 0.9509
1.000 0.7390 0.02303 0.01523 -0.1762 0.8739 1.0000
1.250 0.7751 0.02297 0.01506 -0.1777 0.8705 1.0000
1.500 0.7994 0.02316 0.01519 -0.1771 0.8626 1.0000
1.750 0.8328 0.02309 0.01507 -0.1781 0.8576 1.0000
2.000 0.8693 0.02287 0.01484 -0.1795 0.8536 1.0000
2.250 0.8929 0.02295 0.01493 -0.1786 0.8438 1.0000
2.500 0.9308 0.02254 0.01455 -0.1801 0.8394 1.0000
2.750 0.9530 0.02266 0.01473 -0.1790 0.8291 1.0000
3.000 0.9893 0.02230 0.01443 -0.1802 0.8251 1.0000
3.250 1.0098 0.02252 0.01476 -0.1788 0.8144 1.0000
3.750 1.0655 0.02234 0.01481 -0.1783 0.7990 1.0000
4.000 1.0890 0.02237 0.01500 -0.1773 0.7881 1.0000
4.250 1.1188 0.02202 0.01480 -0.1771 0.7781 1.0000
4.500 1.1453 0.02170 0.01463 -0.1762 0.7630 1.0000
4.750 1.1712 0.02134 0.01446 -0.1750 0.7424 1.0000
5.000 1.2056 0.02064 0.01392 -0.1752 0.7202 1.0000
5.250 1.2425 0.01997 0.01339 -0.1757 0.6908 1.0000
5.500 1.2880 0.01921 0.01271 -0.1777 0.6415 1.0000
5.750 1.3242 0.01959 0.01223 -0.1778 0.4790 1.0000
6.000 1.3206 0.02185 0.01339 -0.1721 0.3250 1.0000
6.250 1.3197 0.02414 0.01484 -0.1676 0.2121 1.0000
6.500 1.3236 0.02645 0.01639 -0.1642 0.1021 1.0000
6.750 1.3301 0.02868 0.01822 -0.1609 0.0476 1.0000
7.000 1.3418 0.03035 0.01989 -0.1582 0.0324 1.0000
7.250 1.3532 0.03199 0.02167 -0.1555 0.0274 1.0000
7.500 1.3640 0.03363 0.02349 -0.1529 0.0238 1.0000
7.750 1.3707 0.03574 0.02577 -0.1498 0.0210 1.0000
8.000 1.3787 0.03797 0.02818 -0.1468 0.0198 1.0000
8.250 1.3916 0.03999 0.03040 -0.1445 0.0186 1.0000
8.500 1.4068 0.04197 0.03254 -0.1427 0.0169 1.0000
8.750 1.4226 0.04426 0.03492 -0.1412 0.0155 1.0000
9.000 1.4499 0.04743 0.03831 -0.1411 0.0148 1.0000
9.250 1.4779 0.05073 0.04205 -0.1407 0.0143 1.0000
9.500 1.4957 0.05407 0.04586 -0.1391 0.0135 1.0000
9.750 1.5053 0.05725 0.04944 -0.1368 0.0128 1.0000
10.000 1.5097 0.06037 0.05289 -0.1341 0.0122 1.0000
10.250 1.5108 0.06384 0.05669 -0.1311 0.0120 1.0000
10.500 1.5071 0.06771 0.06094 -0.1278 0.0119 1.0000
10.750 1.4993 0.07177 0.06537 -0.1245 0.0118 1.0000
11.000 1.4874 0.07610 0.07008 -0.1212 0.0118 1.0000
11.250 1.4721 0.08076 0.07512 -0.1183 0.0118 1.0000
11.500 1.4537 0.08584 0.08058 -0.1159 0.0119 1.0000
11.750 1.4341 0.09128 0.08637 -0.1143 0.0120 1.0000
12.000 1.4129 0.09727 0.09270 -0.1137 0.0121 1.0000
12.250 1.3910 0.10367 0.09940 -0.1143 0.0122 1.0000
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Polar data table (+)
Polar graphs
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