GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il) Reynolds number: 50,000 Max Cl/Cd: 41.11 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe804-il-50000-n5.txt Download as CSV file: xf-goe804-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3846 0.12844 0.12214 -0.0225 1.0000 0.0614
-7.500 -0.3931 0.12763 0.12141 -0.0214 1.0000 0.0615
-7.250 -0.4016 0.12674 0.12060 -0.0203 1.0000 0.0617
-7.000 -0.4070 0.12547 0.11942 -0.0206 1.0000 0.0618
-6.750 -0.3982 0.11944 0.11340 -0.0178 1.0000 0.0627
-6.500 -0.3939 0.11558 0.10957 -0.0161 1.0000 0.0639
-6.250 -0.3937 0.11291 0.10694 -0.0150 1.0000 0.0651
-6.000 -0.3940 0.11052 0.10460 -0.0144 1.0000 0.0663
-5.750 -0.3938 0.10816 0.10229 -0.0142 1.0000 0.0680
-5.500 -0.3926 0.10578 0.09997 -0.0147 1.0000 0.0696
-5.250 -0.3891 0.10360 0.09783 -0.0171 1.0000 0.0722
-5.000 -0.3659 0.10144 0.09566 -0.0285 0.9975 0.0742
-4.750 -0.3481 0.09656 0.09080 -0.0316 0.9939 0.0755
-4.500 -0.3388 0.09245 0.08667 -0.0294 0.9908 0.0788
-4.250 -0.3147 0.08867 0.08285 -0.0345 0.9867 0.0828
-4.000 -0.2591 0.08469 0.07867 -0.0530 0.9811 0.0888
-3.750 -0.2298 0.07983 0.07377 -0.0587 0.9779 0.0899
-3.500 -0.2158 0.07593 0.06988 -0.0583 0.9739 0.0920
-3.250 -0.1844 0.07214 0.06598 -0.0635 0.9703 0.0979
-3.000 -0.0950 0.06372 0.05700 -0.0852 0.9689 0.0613
-2.750 -0.0645 0.05972 0.05293 -0.0889 0.9661 0.0570
-2.500 -0.0010 0.05418 0.04702 -0.1010 0.9645 0.0538
-2.250 0.0614 0.04965 0.04203 -0.1118 0.9630 0.0565
-2.000 0.1311 0.04493 0.03661 -0.1232 0.9626 0.0584
-1.750 0.1944 0.04125 0.03216 -0.1323 0.9620 0.0642
-1.500 0.2487 0.03889 0.02894 -0.1385 0.9607 0.0743
-1.250 0.2914 0.03749 0.02712 -0.1424 0.9586 0.0870
-1.000 0.3348 0.03641 0.02546 -0.1459 0.9566 0.1031
-0.750 0.3709 0.03555 0.02430 -0.1481 0.9536 0.1146
-0.500 0.4015 0.03518 0.02364 -0.1490 0.9492 0.1305
-0.250 0.4335 0.03483 0.02308 -0.1500 0.9456 0.1393
0.000 0.4681 0.03474 0.02281 -0.1516 0.9425 0.1549
0.250 0.4957 0.03473 0.02271 -0.1521 0.9373 0.1711
0.500 0.5276 0.03474 0.02264 -0.1533 0.9326 0.1909
0.750 0.5655 0.03466 0.02270 -0.1560 0.9293 0.2394
1.000 0.5847 0.03313 0.02295 -0.1546 0.9240 1.0000
1.250 0.6130 0.03368 0.02315 -0.1550 0.9177 1.0000
1.500 0.6478 0.03425 0.02345 -0.1568 0.9134 1.0000
1.750 0.6715 0.03479 0.02386 -0.1566 0.9052 1.0000
2.250 0.7358 0.03554 0.02442 -0.1588 0.8883 1.0000
2.500 0.7691 0.03583 0.02465 -0.1599 0.8797 1.0000
2.750 0.8011 0.03613 0.02496 -0.1609 0.8712 1.0000
3.000 0.8261 0.03662 0.02549 -0.1608 0.8622 1.0000
3.250 0.8598 0.03695 0.02588 -0.1621 0.8558 1.0000
3.500 0.8823 0.03749 0.02653 -0.1616 0.8457 1.0000
3.750 0.9174 0.03771 0.02686 -0.1630 0.8394 1.0000
4.000 0.9419 0.03807 0.02740 -0.1626 0.8281 1.0000
4.250 0.9675 0.03833 0.02782 -0.1623 0.8161 1.0000
4.500 0.9958 0.03839 0.02807 -0.1622 0.8038 1.0000
4.750 1.0259 0.03825 0.02818 -0.1621 0.7908 1.0000
5.000 1.0563 0.03798 0.02817 -0.1619 0.7768 1.0000
5.250 1.0859 0.03766 0.02812 -0.1615 0.7620 1.0000
5.500 1.1149 0.03734 0.02815 -0.1609 0.7471 1.0000
5.750 1.1440 0.03704 0.02821 -0.1603 0.7329 1.0000
6.000 1.1708 0.03662 0.02816 -0.1590 0.7149 1.0000
6.250 1.2022 0.03561 0.02760 -0.1578 0.6943 1.0000
6.500 1.2348 0.03403 0.02642 -0.1558 0.6612 1.0000
6.750 1.2644 0.03263 0.02527 -0.1530 0.6022 1.0000
7.000 1.2969 0.03155 0.02324 -0.1493 0.4225 1.0000
7.250 1.2876 0.03456 0.02499 -0.1438 0.2643 1.0000
7.500 1.2830 0.03789 0.02745 -0.1399 0.1426 1.0000
7.750 1.2834 0.04144 0.03031 -0.1367 0.0809 1.0000
8.000 1.2900 0.04437 0.03301 -0.1342 0.0607 1.0000
8.250 1.3006 0.04686 0.03567 -0.1319 0.0503 1.0000
8.500 1.3159 0.04920 0.03833 -0.1299 0.0438 1.0000
8.750 1.3336 0.05159 0.04081 -0.1283 0.0385 1.0000
9.000 1.3665 0.05393 0.04352 -0.1278 0.0343 1.0000
9.250 1.3968 0.05688 0.04658 -0.1279 0.0309 1.0000
9.500 1.4351 0.06090 0.05125 -0.1284 0.0287 1.0000
9.750 1.4579 0.06540 0.05637 -0.1274 0.0279 1.0000
10.000 1.4643 0.06966 0.06118 -0.1248 0.0272 1.0000
10.250 1.4624 0.07381 0.06581 -0.1217 0.0268 1.0000
10.500 1.4549 0.07801 0.07045 -0.1184 0.0263 1.0000
10.750 1.4435 0.08233 0.07519 -0.1153 0.0260 1.0000
11.000 1.4292 0.08686 0.08009 -0.1127 0.0258 1.0000
11.250 1.4125 0.09170 0.08528 -0.1106 0.0257 1.0000
11.500 1.3944 0.09686 0.09076 -0.1093 0.0258 1.0000
11.750 1.3750 0.10242 0.09662 -0.1089 0.0259 1.0000
12.000 1.3546 0.10847 0.10294 -0.1096 0.0260 1.0000
12.250 1.3344 0.11493 0.10963 -0.1114 0.0263 1.0000
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Polar data table (+)
Polar graphs
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