GOE 229 (MVA H.39) AIRFOIL (goe229-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 229 (MVA H.39) AIRFOIL (goe229-il) Reynolds number: 200,000 Max Cl/Cd: 53.83 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe229-il-200000.txt Download as CSV file: xf-goe229-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 229 (MVA H.39) 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 -0.0866 0.10606 0.10277 -0.1014 0.9627 0.0809
-11.250 -0.1144 0.09698 0.09372 -0.1148 0.9560 0.0897
-11.000 -0.0751 0.09598 0.09270 -0.1111 0.9541 0.0925
-10.750 -0.0545 0.09453 0.09123 -0.1107 0.9466 0.0957
-10.500 -0.0902 0.08438 0.08114 -0.1220 0.9384 0.1056
-10.250 -0.0589 0.08487 0.08159 -0.1178 0.9311 0.1076
-10.000 -0.0416 0.08321 0.07991 -0.1172 0.9240 0.1109
-9.750 -0.2719 0.04454 0.03950 -0.1558 0.8914 0.0541
-9.500 -0.2611 0.03811 0.03293 -0.1565 0.8862 0.0499
-9.250 -0.2531 0.03443 0.02866 -0.1568 0.8770 0.0473
-9.000 -0.2306 0.03194 0.02578 -0.1576 0.8722 0.0470
-8.750 -0.2113 0.03053 0.02433 -0.1571 0.8642 0.0482
-8.500 -0.1872 0.02902 0.02265 -0.1573 0.8584 0.0497
-8.250 -0.1607 0.02746 0.02088 -0.1576 0.8539 0.0506
-8.000 -0.1397 0.02629 0.01958 -0.1568 0.8456 0.0513
-7.750 -0.1127 0.02509 0.01822 -0.1568 0.8404 0.0524
-7.500 -0.0875 0.02436 0.01734 -0.1566 0.8336 0.0539
-7.250 -0.0645 0.02301 0.01596 -0.1559 0.8267 0.0553
-7.000 -0.0382 0.02181 0.01477 -0.1557 0.8219 0.0569
-6.750 -0.0163 0.02109 0.01409 -0.1551 0.8135 0.0586
-6.500 0.0110 0.02030 0.01326 -0.1554 0.8076 0.0613
-6.250 0.0374 0.01966 0.01255 -0.1556 0.8008 0.0635
-6.000 0.0645 0.01903 0.01185 -0.1560 0.7934 0.0651
-5.750 0.0953 0.01805 0.01078 -0.1574 0.7881 0.0691
-5.500 0.1211 0.01753 0.01023 -0.1577 0.7789 0.0739
-5.250 0.1525 0.01690 0.00950 -0.1588 0.7728 0.0813
-5.000 0.1799 0.01634 0.00898 -0.1592 0.7642 0.1040
-4.750 0.2101 0.01478 0.00831 -0.1616 0.7575 0.3285
-4.500 0.2385 0.01509 0.00858 -0.1615 0.7495 0.3715
-4.250 0.2681 0.01537 0.00872 -0.1615 0.7416 0.3929
-4.000 0.2958 0.01566 0.00895 -0.1611 0.7327 0.4059
-3.750 0.3244 0.01593 0.00916 -0.1607 0.7242 0.4177
-3.500 0.3514 0.01613 0.00926 -0.1604 0.7141 0.4287
-3.250 0.3806 0.01625 0.00928 -0.1602 0.7055 0.4360
-3.000 0.4068 0.01634 0.00927 -0.1599 0.6945 0.4450
-2.750 0.4339 0.01657 0.00950 -0.1593 0.6859 0.4529
-2.500 0.4612 0.01666 0.00948 -0.1592 0.6764 0.4622
-2.250 0.4873 0.01690 0.00975 -0.1584 0.6679 0.4697
-2.000 0.5152 0.01692 0.00959 -0.1584 0.6576 0.4782
-1.750 0.5400 0.01684 0.00952 -0.1577 0.6457 0.4825
-1.500 0.5662 0.01680 0.00939 -0.1573 0.6342 0.4870
-1.250 0.5933 0.01672 0.00917 -0.1573 0.6236 0.4920
-1.000 0.6201 0.01661 0.00894 -0.1574 0.6126 0.4965
-0.750 0.6459 0.01654 0.00882 -0.1570 0.6021 0.4997
-0.500 0.6714 0.01652 0.00870 -0.1566 0.5904 0.5032
-0.250 0.6970 0.01649 0.00862 -0.1564 0.5793 0.5071
0.000 0.7237 0.01650 0.00849 -0.1564 0.5697 0.5118
0.250 0.7491 0.01648 0.00839 -0.1561 0.5589 0.5154
0.500 0.7734 0.01650 0.00838 -0.1556 0.5471 0.5185
0.750 0.7981 0.01657 0.00837 -0.1551 0.5364 0.5222
1.000 0.8218 0.01667 0.00834 -0.1546 0.5235 0.5266
1.250 0.8449 0.01678 0.00832 -0.1540 0.5082 0.5311
1.500 0.8661 0.01687 0.00837 -0.1529 0.4918 0.5342
1.750 0.8871 0.01702 0.00846 -0.1519 0.4751 0.5376
2.000 0.9082 0.01719 0.00855 -0.1509 0.4580 0.5417
2.250 0.9290 0.01741 0.00865 -0.1500 0.4399 0.5466
2.500 0.9485 0.01762 0.00879 -0.1488 0.4175 0.5505
2.750 0.9630 0.01801 0.00904 -0.1467 0.3864 0.5542
3.000 0.9679 0.01870 0.00947 -0.1430 0.3417 0.5579
3.250 0.9561 0.02054 0.01074 -0.1374 0.2565 0.5611
3.500 0.9641 0.02166 0.01160 -0.1350 0.2242 0.5655
3.750 0.9767 0.02244 0.01232 -0.1332 0.2069 0.5691
4.000 0.9911 0.02315 0.01301 -0.1317 0.1938 0.5738
4.250 1.0059 0.02389 0.01369 -0.1303 0.1799 0.5793
4.750 1.0188 0.02644 0.01594 -0.1259 0.1197 0.5882
5.000 1.0317 0.02737 0.01687 -0.1246 0.1155 0.5935
5.250 1.0464 0.02824 0.01774 -0.1235 0.1125 0.5997
5.500 1.0616 0.02904 0.01860 -0.1225 0.1107 0.6049
5.750 1.0772 0.02985 0.01946 -0.1216 0.1095 0.6115
6.000 1.0928 0.03071 0.02036 -0.1207 0.1084 0.6190
6.250 1.1073 0.03161 0.02136 -0.1197 0.1073 0.6258
6.500 1.1219 0.03259 0.02237 -0.1189 0.1063 0.6344
6.750 1.1360 0.03357 0.02344 -0.1180 0.1054 0.6417
7.000 1.1499 0.03463 0.02455 -0.1172 0.1046 0.6513
7.250 1.1635 0.03567 0.02570 -0.1163 0.1040 0.6601
7.500 1.1772 0.03676 0.02687 -0.1156 0.1036 0.6712
7.750 1.1909 0.03786 0.02806 -0.1148 0.1033 0.6839
8.000 1.2044 0.03898 0.02929 -0.1141 0.1032 0.6977
8.250 1.2179 0.04013 0.03057 -0.1135 0.1030 0.7140
8.500 1.2310 0.04130 0.03187 -0.1128 0.1030 0.7344
8.750 1.2437 0.04241 0.03318 -0.1120 0.1030 0.7645
9.000 1.2482 0.04325 0.03439 -0.1098 0.1028 1.0000
9.250 1.2594 0.04487 0.03603 -0.1093 0.1020 1.0000
9.500 1.2692 0.04660 0.03777 -0.1088 0.1008 1.0000
9.750 1.2782 0.04841 0.03959 -0.1082 0.0996 1.0000
10.000 1.2902 0.04993 0.04116 -0.1077 0.0987 1.0000
10.250 1.3015 0.05154 0.04282 -0.1073 0.0977 1.0000
10.500 1.3121 0.05322 0.04456 -0.1068 0.0961 1.0000
10.750 1.3217 0.05502 0.04641 -0.1064 0.0942 1.0000
11.000 1.3301 0.05695 0.04838 -0.1059 0.0927 1.0000
11.250 1.3380 0.05895 0.05043 -0.1054 0.0914 1.0000
11.500 1.3444 0.06115 0.05268 -0.1049 0.0899 1.0000
11.750 1.3557 0.06282 0.05443 -0.1046 0.0874 1.0000
12.000 1.3657 0.06468 0.05644 -0.1043 0.0677 1.0000
12.250 1.3607 0.06819 0.05976 -0.1037 0.0635 1.0000
12.500 1.3589 0.07147 0.06314 -0.1032 0.0620 1.0000
12.750 1.3573 0.07478 0.06658 -0.1028 0.0610 1.0000
13.000 1.3569 0.07799 0.06990 -0.1026 0.0601 1.0000
13.250 1.3571 0.08118 0.07321 -0.1024 0.0593 1.0000
13.500 1.3561 0.08454 0.07671 -0.1023 0.0585 1.0000
13.750 1.3513 0.08842 0.08074 -0.1022 0.0574 1.0000
14.000 1.3418 0.09300 0.08548 -0.1022 0.0562 1.0000
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