GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.41 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe147-il-1000000-n5.txt Download as CSV file: xf-goe147-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 147 (MVA H.6) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5186 0.10631 0.10478 0.0173 1.0000 0.0039
-9.250 -0.5181 0.10150 0.09998 0.0151 1.0000 0.0039
-9.000 -0.6422 0.05206 0.05027 -0.0303 1.0000 0.0039
-8.750 -0.6321 0.02955 0.02690 -0.0522 1.0000 0.0039
-8.500 -0.6095 0.02249 0.01939 -0.0559 1.0000 0.0039
-8.250 -0.5849 0.01906 0.01558 -0.0573 1.0000 0.0040
-8.000 -0.5590 0.01714 0.01342 -0.0579 1.0000 0.0042
-7.750 -0.5323 0.01598 0.01210 -0.0582 1.0000 0.0043
-7.500 -0.5052 0.01506 0.01106 -0.0583 1.0000 0.0045
-7.250 -0.4779 0.01426 0.01013 -0.0584 1.0000 0.0046
-7.000 -0.4504 0.01352 0.00929 -0.0584 1.0000 0.0048
-6.750 -0.4229 0.01284 0.00849 -0.0584 1.0000 0.0050
-6.500 -0.3918 0.01217 0.00772 -0.0592 0.9878 0.0052
-6.250 -0.3579 0.01157 0.00699 -0.0605 0.9567 0.0055
-6.000 -0.3309 0.01126 0.00652 -0.0600 0.9119 0.0058
-5.750 -0.3059 0.01100 0.00604 -0.0591 0.8702 0.0060
-5.500 -0.2797 0.01050 0.00527 -0.0586 0.8274 0.0066
-5.250 -0.2528 0.01027 0.00483 -0.0582 0.7841 0.0070
-5.000 -0.2252 0.01007 0.00442 -0.0580 0.7422 0.0075
-4.750 -0.1974 0.00989 0.00403 -0.0578 0.7009 0.0080
-4.500 -0.1694 0.00975 0.00368 -0.0577 0.6578 0.0085
-4.250 -0.1412 0.00957 0.00330 -0.0576 0.6211 0.0092
-4.000 -0.1129 0.00936 0.00297 -0.0575 0.5937 0.0106
-3.750 -0.0845 0.00922 0.00272 -0.0575 0.5735 0.0119
-3.500 -0.0560 0.00908 0.00250 -0.0574 0.5601 0.0129
-3.250 -0.0274 0.00887 0.00222 -0.0574 0.5473 0.0163
-3.000 0.0012 0.00874 0.00203 -0.0574 0.5350 0.0201
-2.750 0.0297 0.00857 0.00183 -0.0573 0.5228 0.0287
-2.500 0.0582 0.00838 0.00161 -0.0574 0.5087 0.0438
-2.250 0.0866 0.00830 0.00164 -0.0574 0.4939 0.0844
-2.000 0.1152 0.00831 0.00160 -0.0573 0.4823 0.0879
-1.750 0.1438 0.00834 0.00160 -0.0573 0.4693 0.0916
-1.500 0.1723 0.00842 0.00162 -0.0572 0.4535 0.0951
-1.250 0.2008 0.00849 0.00159 -0.0571 0.4336 0.0965
-1.000 0.2292 0.00854 0.00153 -0.0571 0.4080 0.0969
-0.750 0.2574 0.00868 0.00152 -0.0571 0.3723 0.0975
-0.500 0.2856 0.00879 0.00149 -0.0571 0.3407 0.0988
-0.250 0.3139 0.00884 0.00144 -0.0571 0.3192 0.0994
0.000 0.3422 0.00890 0.00141 -0.0571 0.3018 0.1002
0.500 0.3991 0.00897 0.00138 -0.0571 0.2766 0.1019
0.750 0.4275 0.00901 0.00139 -0.0571 0.2670 0.1028
1.250 0.4842 0.00910 0.00142 -0.0571 0.2505 0.1050
1.500 0.5125 0.00918 0.00146 -0.0570 0.2411 0.1063
1.750 0.5408 0.00923 0.00150 -0.0570 0.2331 0.1074
2.000 0.5691 0.00931 0.00154 -0.0570 0.2262 0.1083
2.250 0.5974 0.00937 0.00160 -0.0570 0.2201 0.1093
2.750 0.6537 0.00952 0.00173 -0.0570 0.2079 0.1109
3.000 0.6818 0.00962 0.00181 -0.0569 0.2010 0.1121
3.250 0.7099 0.00970 0.00191 -0.0569 0.1950 0.1151
3.500 0.7379 0.00980 0.00201 -0.0569 0.1871 0.1189
3.750 0.7659 0.00991 0.00212 -0.0569 0.1791 0.1236
4.000 0.7938 0.01001 0.00228 -0.0569 0.1687 0.1591
4.250 0.8214 0.01017 0.00245 -0.0569 0.1558 0.1942
4.500 0.8489 0.01036 0.00263 -0.0569 0.1433 0.2097
4.750 0.8766 0.01051 0.00282 -0.0569 0.1356 0.2312
5.000 0.9043 0.01061 0.00303 -0.0569 0.1294 0.2881
5.500 0.9542 0.00956 0.00348 -0.0560 0.1243 1.0000
5.750 0.9814 0.00983 0.00372 -0.0559 0.1168 1.0000
6.000 1.0088 0.01002 0.00392 -0.0558 0.1137 1.0000
6.250 1.0360 0.01025 0.00414 -0.0557 0.1093 1.0000
6.500 1.0629 0.01054 0.00441 -0.0556 0.1029 1.0000
6.750 1.0901 0.01075 0.00463 -0.0556 0.0989 1.0000
7.000 1.1165 0.01110 0.00492 -0.0554 0.0866 1.0000
7.250 1.1380 0.01247 0.00594 -0.0549 0.0242 1.0000
7.500 1.1633 0.01302 0.00646 -0.0546 0.0138 1.0000
7.750 1.1890 0.01344 0.00690 -0.0544 0.0104 1.0000
8.000 1.2145 0.01388 0.00736 -0.0541 0.0086 1.0000
8.250 1.2398 0.01435 0.00786 -0.0538 0.0073 1.0000
8.500 1.2652 0.01477 0.00832 -0.0535 0.0066 1.0000
8.750 1.2901 0.01524 0.00883 -0.0532 0.0059 1.0000
9.000 1.3142 0.01585 0.00948 -0.0528 0.0051 1.0000
9.250 1.3388 0.01632 0.01000 -0.0525 0.0048 1.0000
9.500 1.3629 0.01685 0.01060 -0.0521 0.0044 1.0000
9.750 1.3865 0.01741 0.01122 -0.0517 0.0041 1.0000
10.000 1.4096 0.01803 0.01189 -0.0512 0.0038 1.0000
10.250 1.4314 0.01882 0.01275 -0.0506 0.0035 1.0000
10.500 1.4528 0.01960 0.01361 -0.0499 0.0033 1.0000
10.750 1.4743 0.02032 0.01442 -0.0493 0.0032 1.0000
11.000 1.4949 0.02111 0.01529 -0.0486 0.0030 1.0000
11.250 1.5147 0.02195 0.01621 -0.0478 0.0029 1.0000
11.500 1.5337 0.02280 0.01715 -0.0470 0.0027 1.0000
11.750 1.5521 0.02367 0.01811 -0.0461 0.0026 1.0000
12.000 1.5694 0.02459 0.01910 -0.0451 0.0025 1.0000
12.250 1.5847 0.02563 0.02023 -0.0440 0.0023 1.0000
12.500 1.5963 0.02695 0.02165 -0.0425 0.0022 1.0000
12.750 1.6010 0.02870 0.02353 -0.0404 0.0021 1.0000
13.000 1.6035 0.03016 0.02510 -0.0379 0.0021 1.0000
13.250 1.6043 0.03191 0.02696 -0.0360 0.0021 1.0000
13.500 1.6020 0.03435 0.02954 -0.0351 0.0020 1.0000
13.750 1.5991 0.03744 0.03277 -0.0353 0.0020 1.0000
14.000 1.5939 0.04142 0.03689 -0.0368 0.0020 1.0000
14.250 1.5854 0.04640 0.04203 -0.0392 0.0020 1.0000
14.500 1.5727 0.05232 0.04811 -0.0423 0.0019 1.0000
14.750 1.5550 0.05906 0.05501 -0.0455 0.0019 1.0000
15.000 1.5327 0.06651 0.06261 -0.0488 0.0019 1.0000
15.250 1.5070 0.07464 0.07089 -0.0524 0.0020 1.0000
15.500 1.4798 0.08310 0.07950 -0.0559 0.0020 1.0000
15.750 1.4522 0.09164 0.08817 -0.0594 0.0020 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 147 (MVA H.6) AIRFOIL (goe147-il)