GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il) Reynolds number: 100,000 Max Cl/Cd: 45.61 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe228-il-100000.txt Download as CSV file: xf-goe228-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 228 (MVA H.38) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.0987 0.11024 0.10574 -0.0878 0.9242 0.1591
-8.500 -0.0410 0.10489 0.10030 -0.0891 0.9231 0.1639
-8.250 -0.0400 0.10313 0.09855 -0.0896 0.9129 0.1711
-8.000 -0.0360 0.09928 0.09471 -0.0946 0.9068 0.1766
-7.750 0.0087 0.09496 0.09032 -0.0985 0.9051 0.1828
-7.250 -0.1881 0.05527 0.04980 -0.1372 0.8608 0.1000
-7.000 -0.1472 0.04876 0.04279 -0.1461 0.8566 0.0989
-6.750 -0.1112 0.04441 0.03776 -0.1523 0.8494 0.0996
-6.500 -0.0746 0.04117 0.03409 -0.1565 0.8421 0.1018
-6.250 -0.0254 0.03858 0.03128 -0.1611 0.8388 0.1048
-6.000 0.0044 0.03710 0.02957 -0.1623 0.8299 0.1074
-5.750 0.0487 0.03535 0.02738 -0.1656 0.8241 0.1126
-5.500 0.0997 0.03325 0.02529 -0.1696 0.8216 0.1193
-5.250 0.1292 0.03235 0.02421 -0.1700 0.8125 0.1257
-5.000 0.1702 0.03091 0.02283 -0.1721 0.8069 0.1368
-4.750 0.2183 0.02924 0.02116 -0.1752 0.8040 0.1549
-4.500 0.2467 0.02848 0.02049 -0.1755 0.7944 0.1761
-4.250 0.2882 0.02736 0.01963 -0.1777 0.7888 0.2165
-4.000 0.3342 0.02679 0.01924 -0.1800 0.7853 0.2873
-3.750 0.3561 0.02734 0.01975 -0.1786 0.7733 0.3292
-3.500 0.3946 0.02709 0.01954 -0.1791 0.7687 0.3621
-3.250 0.4189 0.02722 0.01959 -0.1781 0.7581 0.3840
-3.000 0.4557 0.02673 0.01904 -0.1787 0.7522 0.4051
-2.750 0.4833 0.02661 0.01889 -0.1781 0.7433 0.4209
-2.500 0.5144 0.02629 0.01857 -0.1778 0.7355 0.4368
-2.250 0.5447 0.02609 0.01834 -0.1774 0.7278 0.4528
-2.000 0.5727 0.02594 0.01815 -0.1768 0.7186 0.4680
-1.750 0.6045 0.02567 0.01778 -0.1770 0.7109 0.4830
-1.500 0.6331 0.02550 0.01754 -0.1767 0.7015 0.4954
-1.250 0.6631 0.02527 0.01724 -0.1767 0.6934 0.5057
-1.000 0.6949 0.02500 0.01680 -0.1774 0.6844 0.5180
-0.750 0.7226 0.02489 0.01667 -0.1769 0.6758 0.5271
-0.500 0.7546 0.02463 0.01626 -0.1776 0.6671 0.5382
-0.250 0.7826 0.02459 0.01616 -0.1775 0.6585 0.5472
0.000 0.8134 0.02445 0.01590 -0.1780 0.6501 0.5580
0.250 0.8423 0.02446 0.01583 -0.1782 0.6418 0.5688
0.500 0.8708 0.02442 0.01571 -0.1783 0.6333 0.5790
0.750 0.9010 0.02446 0.01563 -0.1788 0.6255 0.5924
1.000 0.9267 0.02459 0.01575 -0.1784 0.6170 0.6049
1.250 0.9594 0.02454 0.01557 -0.1792 0.6106 0.6188
1.500 0.9803 0.02493 0.01602 -0.1783 0.6018 0.6329
1.750 1.0137 0.02487 0.01584 -0.1792 0.5960 0.6514
2.000 1.0335 0.02535 0.01640 -0.1781 0.5880 0.6694
2.250 1.0612 0.02546 0.01647 -0.1781 0.5814 0.6914
2.500 1.0913 0.02555 0.01650 -0.1785 0.5758 0.7161
2.750 1.1080 0.02604 0.01712 -0.1769 0.5681 0.7406
3.000 1.1361 0.02605 0.01710 -0.1768 0.5628 0.7717
3.250 1.1592 0.02630 0.01741 -0.1760 0.5576 0.8061
3.500 1.1711 0.02676 0.01809 -0.1734 0.5513 0.8478
3.750 1.1950 0.02677 0.01818 -0.1728 0.5465 1.0000
4.000 1.2379 0.02714 0.01829 -0.1760 0.5426 1.0000
4.250 1.2497 0.02848 0.01977 -0.1746 0.5362 1.0000
4.500 1.2758 0.02919 0.02042 -0.1750 0.5310 1.0000
4.750 1.3110 0.02950 0.02058 -0.1765 0.5269 1.0000
5.000 1.3297 0.03053 0.02163 -0.1757 0.5217 1.0000
5.250 1.3439 0.03164 0.02280 -0.1742 0.5160 1.0000
5.500 1.3723 0.03213 0.02323 -0.1747 0.5117 1.0000
5.750 1.4100 0.03235 0.02328 -0.1764 0.5082 1.0000
6.000 1.4102 0.03413 0.02527 -0.1730 0.5031 1.0000
6.250 1.4203 0.03548 0.02671 -0.1710 0.4983 1.0000
6.500 1.4456 0.03612 0.02734 -0.1710 0.4946 1.0000
6.750 1.4818 0.03636 0.02748 -0.1724 0.4917 1.0000
7.000 1.4872 0.03812 0.02936 -0.1699 0.4880 1.0000
7.250 1.4539 0.04171 0.03325 -0.1626 0.4828 1.0000
7.500 1.4569 0.04340 0.03501 -0.1598 0.4789 1.0000
7.750 1.4943 0.04341 0.03499 -0.1613 0.4760 1.0000
8.000 1.5463 0.04290 0.03438 -0.1646 0.4737 1.0000
10.000 0.8943 0.14562 0.13864 -0.1466 0.4621 1.0000
10.250 0.9379 0.14676 0.13978 -0.1465 0.4570 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 228 (MVA H.38) AIRFOIL (goe228-il)