GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il) Reynolds number: 200,000 Max Cl/Cd: 72.97 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe223-il-200000.txt Download as CSV file: xf-goe223-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 223 (MVA H.34) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1160 0.10437 0.10092 -0.1015 0.9621 0.0857
-11.250 -0.0888 0.10297 0.09949 -0.1013 0.9580 0.0886
-11.000 -0.0822 0.09946 0.09596 -0.1041 0.9521 0.0938
-10.750 -0.1063 0.09178 0.08834 -0.1108 0.9435 0.0988
-10.500 -0.0844 0.09070 0.08722 -0.1088 0.9377 0.1005
-10.250 -0.0737 0.08872 0.08524 -0.1083 0.9299 0.1029
-10.000 -0.1310 0.07685 0.07345 -0.1206 0.9197 0.1130
-9.750 -0.1062 0.07684 0.07341 -0.1168 0.9140 0.1142
-9.500 -0.2913 0.04346 0.03817 -0.1522 0.8907 0.0622
-9.250 -0.2761 0.03905 0.03382 -0.1516 0.8844 0.0588
-9.000 -0.2640 0.03460 0.02840 -0.1530 0.8788 0.0534
-8.750 -0.2415 0.03220 0.02577 -0.1533 0.8748 0.0536
-8.500 -0.2220 0.03032 0.02376 -0.1529 0.8676 0.0540
-8.250 -0.1967 0.02856 0.02182 -0.1529 0.8632 0.0542
-8.000 -0.1695 0.02695 0.02004 -0.1530 0.8598 0.0543
-7.750 -0.1479 0.02584 0.01887 -0.1523 0.8525 0.0546
-7.500 -0.1221 0.02470 0.01769 -0.1521 0.8475 0.0557
-7.250 -0.0943 0.02366 0.01658 -0.1521 0.8438 0.0570
-7.000 -0.0714 0.02290 0.01579 -0.1514 0.8363 0.0578
-6.750 -0.0451 0.02200 0.01484 -0.1511 0.8307 0.0585
-6.500 -0.0170 0.02113 0.01390 -0.1510 0.8262 0.0594
-6.250 0.0066 0.02053 0.01329 -0.1505 0.8176 0.0604
-6.000 0.0353 0.01985 0.01251 -0.1507 0.8120 0.0619
-5.750 0.0609 0.01902 0.01171 -0.1509 0.8046 0.0638
-5.500 0.0891 0.01831 0.01097 -0.1514 0.7974 0.0658
-5.250 0.1189 0.01771 0.01027 -0.1521 0.7910 0.0682
-5.000 0.1469 0.01722 0.00970 -0.1524 0.7819 0.0712
-4.750 0.1778 0.01661 0.00899 -0.1532 0.7752 0.0770
-4.500 0.2058 0.01610 0.00848 -0.1536 0.7648 0.0901
-4.250 0.2362 0.01438 0.00759 -0.1559 0.7563 0.3057
-4.000 0.2654 0.01448 0.00763 -0.1558 0.7460 0.3607
-3.750 0.2934 0.01471 0.00781 -0.1555 0.7350 0.3833
-3.500 0.3229 0.01492 0.00789 -0.1553 0.7258 0.4002
-3.250 0.3504 0.01512 0.00798 -0.1550 0.7134 0.4136
-3.000 0.3777 0.01531 0.00817 -0.1546 0.7019 0.4228
-2.750 0.4068 0.01538 0.00805 -0.1547 0.6920 0.4318
-2.500 0.4339 0.01546 0.00811 -0.1544 0.6806 0.4377
-2.250 0.4623 0.01560 0.00808 -0.1545 0.6700 0.4467
-2.000 0.4900 0.01576 0.00820 -0.1541 0.6614 0.4546
-1.750 0.5173 0.01592 0.00827 -0.1541 0.6509 0.4636
-1.500 0.5444 0.01610 0.00844 -0.1537 0.6428 0.4719
-1.250 0.5720 0.01627 0.00852 -0.1536 0.6339 0.4812
-1.000 0.6001 0.01629 0.00846 -0.1537 0.6270 0.4862
-0.750 0.6274 0.01630 0.00843 -0.1537 0.6190 0.4897
-0.250 0.6844 0.01636 0.00825 -0.1543 0.6051 0.4986
0.000 0.7129 0.01634 0.00813 -0.1546 0.5988 0.5019
0.250 0.7404 0.01639 0.00816 -0.1547 0.5924 0.5052
0.500 0.7678 0.01645 0.00818 -0.1548 0.5858 0.5093
0.750 0.7974 0.01655 0.00813 -0.1553 0.5807 0.5142
1.000 0.8248 0.01663 0.00819 -0.1555 0.5752 0.5185
1.250 0.8519 0.01669 0.00826 -0.1555 0.5698 0.5219
1.500 0.8808 0.01681 0.00830 -0.1558 0.5649 0.5261
1.750 0.9081 0.01695 0.00842 -0.1560 0.5600 0.5312
2.000 0.9354 0.01705 0.00852 -0.1561 0.5549 0.5362
2.250 0.9631 0.01717 0.00863 -0.1562 0.5504 0.5405
2.500 0.9919 0.01735 0.00876 -0.1566 0.5462 0.5455
2.750 1.0182 0.01750 0.00894 -0.1566 0.5418 0.5511
3.000 1.0450 0.01762 0.00911 -0.1566 0.5374 0.5559
3.250 1.0728 0.01779 0.00927 -0.1568 0.5333 0.5617
3.500 1.1012 0.01802 0.00944 -0.1572 0.5291 0.5686
3.750 1.1252 0.01814 0.00968 -0.1567 0.5238 0.5740
4.000 1.1514 0.01828 0.00986 -0.1566 0.5187 0.5804
4.250 1.1801 0.01849 0.01000 -0.1570 0.5148 0.5879
4.500 1.2054 0.01869 0.01031 -0.1568 0.5110 0.5946
4.750 1.2296 0.01888 0.01059 -0.1564 0.5062 0.6035
5.000 1.2549 0.01902 0.01079 -0.1561 0.5013 0.6113
5.500 1.3051 0.01943 0.01131 -0.1557 0.4925 0.6301
5.750 1.3280 0.01960 0.01158 -0.1551 0.4872 0.6409
6.000 1.3532 0.01976 0.01179 -0.1548 0.4828 0.6530
6.250 1.3793 0.01996 0.01203 -0.1547 0.4787 0.6660
6.500 1.3988 0.02015 0.01242 -0.1536 0.4738 0.6801
6.750 1.4206 0.02031 0.01269 -0.1528 0.4688 0.6964
7.000 1.4448 0.02043 0.01287 -0.1523 0.4643 0.7153
7.250 1.4646 0.02062 0.01323 -0.1512 0.4593 0.7375
7.500 1.4820 0.02074 0.01356 -0.1497 0.4537 0.7652
7.750 1.4999 0.02071 0.01374 -0.1480 0.4487 0.8228
8.000 1.5155 0.02077 0.01397 -0.1460 0.4435 1.0000
8.250 1.5278 0.02113 0.01441 -0.1438 0.4366 1.0000
8.500 1.5430 0.02144 0.01467 -0.1420 0.4294 1.0000
8.750 1.5509 0.02197 0.01533 -0.1393 0.4200 1.0000
9.000 1.5605 0.02252 0.01589 -0.1369 0.4102 1.0000
9.250 1.5681 0.02320 0.01658 -0.1343 0.3987 1.0000
9.500 1.5748 0.02406 0.01749 -0.1318 0.3853 1.0000
9.750 1.5810 0.02505 0.01849 -0.1295 0.3706 1.0000
10.000 1.5846 0.02628 0.01969 -0.1270 0.3536 1.0000
10.250 1.5858 0.02779 0.02114 -0.1244 0.3342 1.0000
10.500 1.5838 0.02963 0.02291 -0.1217 0.3140 1.0000
10.750 1.5802 0.03174 0.02493 -0.1191 0.2965 1.0000
11.000 1.5772 0.03393 0.02705 -0.1167 0.2828 1.0000
11.250 1.5746 0.03618 0.02927 -0.1146 0.2719 1.0000
11.500 1.5719 0.03855 0.03160 -0.1125 0.2625 1.0000
11.750 1.5729 0.04072 0.03379 -0.1109 0.2544 1.0000
12.000 1.5698 0.04331 0.03635 -0.1092 0.2465 1.0000
12.250 1.5699 0.04572 0.03881 -0.1078 0.2379 1.0000
12.500 1.5667 0.04848 0.04155 -0.1064 0.2308 1.0000
12.750 1.5695 0.05081 0.04396 -0.1054 0.2237 1.0000
13.000 1.5672 0.05367 0.04683 -0.1043 0.2167 1.0000
13.250 1.5687 0.05624 0.04948 -0.1035 0.2098 1.0000
13.500 1.5663 0.05928 0.05256 -0.1027 0.2021 1.0000
13.750 1.5654 0.06229 0.05565 -0.1021 0.1930 1.0000
14.000 1.5612 0.06573 0.05912 -0.1015 0.1839 1.0000
14.250 1.5601 0.06893 0.06240 -0.1012 0.1696 1.0000
14.500 1.5492 0.07333 0.06674 -0.1009 0.1446 1.0000
14.750 1.5308 0.07873 0.07200 -0.1007 0.1319 1.0000
15.000 1.5183 0.08342 0.07664 -0.1005 0.1251 1.0000
15.250 1.5070 0.08796 0.08119 -0.1004 0.1190 1.0000
15.500 1.4985 0.09219 0.08545 -0.1003 0.1132 1.0000
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Polar data table (+)
Polar graphs
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