GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il) Reynolds number: 100,000 Max Cl/Cd: 53.72 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe143-il-100000.txt Download as CSV file: xf-goe143-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 143 (MVA H.20) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4031 0.10187 0.09693 -0.0082 1.0000 0.0716
-8.000 -0.4008 0.09930 0.09442 -0.0109 1.0000 0.0744
-7.750 -0.4039 0.09806 0.09329 -0.0188 1.0000 0.0761
-7.500 -0.3959 0.09526 0.09050 -0.0310 1.0000 0.0768
-7.250 -0.3875 0.08911 0.08439 -0.0184 1.0000 0.0791
-7.000 -0.3775 0.08576 0.08106 -0.0181 1.0000 0.0817
-6.750 -0.3681 0.08250 0.07783 -0.0205 1.0000 0.0848
-6.500 -0.3547 0.07939 0.07470 -0.0294 1.0000 0.0894
-6.250 -0.3400 0.07515 0.07038 -0.0381 1.0000 0.0913
-6.000 -0.3350 0.07151 0.06687 -0.0326 1.0000 0.0933
-5.750 -0.3254 0.06874 0.06414 -0.0315 1.0000 0.0975
-5.500 -0.3007 0.06515 0.06027 -0.0429 1.0000 0.1052
-5.250 -0.2958 0.06161 0.05687 -0.0390 1.0000 0.1069
-5.000 -0.2863 0.05898 0.05429 -0.0375 1.0000 0.1105
-4.750 -0.2622 0.05564 0.05065 -0.0438 1.0000 0.1197
-4.500 -0.2561 0.05294 0.04810 -0.0407 1.0000 0.1228
-4.250 -0.2357 0.05024 0.04519 -0.0436 1.0000 0.1347
-4.000 -0.2266 0.04795 0.04299 -0.0415 1.0000 0.1396
-3.750 -0.2069 0.04533 0.04020 -0.0432 1.0000 0.1512
-3.500 -0.1877 0.04318 0.03791 -0.0442 1.0000 0.1652
-3.250 -0.1700 0.04120 0.03585 -0.0445 1.0000 0.1803
-3.000 -0.1546 0.03927 0.03395 -0.0439 1.0000 0.1972
-2.750 -0.1381 0.03766 0.03236 -0.0434 1.0000 0.2177
-1.500 0.1190 0.02435 0.01634 -0.0679 0.9719 0.1304
-1.250 0.1682 0.02260 0.01431 -0.0717 0.9616 0.1257
-1.000 0.2194 0.02130 0.01274 -0.0758 0.9518 0.1267
-0.750 0.2719 0.02000 0.01125 -0.0799 0.9420 0.1260
-0.500 0.3173 0.01897 0.01014 -0.0825 0.9287 0.1285
-0.250 0.3595 0.01797 0.00915 -0.0845 0.9140 0.1366
0.000 0.3977 0.01708 0.00834 -0.0856 0.8978 0.1438
0.250 0.4307 0.01627 0.00761 -0.0854 0.8793 0.1520
0.500 0.4592 0.01569 0.00709 -0.0844 0.8571 0.1685
0.750 0.4883 0.01509 0.00658 -0.0834 0.8359 0.2035
1.000 0.5121 0.01297 0.00623 -0.0810 0.8110 1.0000
1.250 0.5374 0.01306 0.00602 -0.0793 0.7847 1.0000
1.500 0.5625 0.01318 0.00589 -0.0778 0.7583 1.0000
1.750 0.5875 0.01334 0.00585 -0.0765 0.7311 1.0000
2.000 0.6129 0.01353 0.00586 -0.0754 0.7042 1.0000
2.250 0.6386 0.01376 0.00591 -0.0744 0.6795 1.0000
2.500 0.6644 0.01400 0.00596 -0.0735 0.6564 1.0000
2.750 0.6901 0.01428 0.00609 -0.0726 0.6322 1.0000
3.000 0.7157 0.01456 0.00618 -0.0717 0.6097 1.0000
3.250 0.7409 0.01484 0.00633 -0.0708 0.5843 1.0000
3.500 0.7661 0.01514 0.00647 -0.0699 0.5603 1.0000
3.750 0.7915 0.01546 0.00667 -0.0692 0.5384 1.0000
4.000 0.8174 0.01583 0.00695 -0.0686 0.5203 1.0000
4.250 0.8433 0.01622 0.00727 -0.0681 0.5033 1.0000
4.500 0.8691 0.01660 0.00763 -0.0675 0.4854 1.0000
4.750 0.8946 0.01698 0.00802 -0.0670 0.4673 1.0000
5.000 0.9198 0.01736 0.00837 -0.0664 0.4488 1.0000
5.250 0.9448 0.01775 0.00870 -0.0657 0.4300 1.0000
5.500 0.9694 0.01813 0.00911 -0.0650 0.4088 1.0000
5.750 0.9936 0.01852 0.00951 -0.0642 0.3860 1.0000
6.000 1.0170 0.01893 0.00994 -0.0633 0.3586 1.0000
6.250 1.0394 0.01945 0.01038 -0.0623 0.3268 1.0000
6.500 1.0614 0.02018 0.01095 -0.0613 0.2951 1.0000
6.750 1.0840 0.02103 0.01174 -0.0604 0.2694 1.0000
7.000 1.1068 0.02182 0.01241 -0.0597 0.2514 1.0000
7.250 1.1293 0.02250 0.01307 -0.0589 0.2349 1.0000
7.500 1.1515 0.02312 0.01371 -0.0582 0.2199 1.0000
7.750 1.1735 0.02377 0.01438 -0.0575 0.2072 1.0000
8.000 1.1959 0.02439 0.01514 -0.0568 0.1962 1.0000
8.250 1.2175 0.02500 0.01589 -0.0560 0.1849 1.0000
8.500 1.2381 0.02554 0.01656 -0.0552 0.1722 1.0000
8.750 1.2580 0.02607 0.01727 -0.0543 0.1581 1.0000
9.000 1.2761 0.02673 0.01801 -0.0533 0.1392 1.0000
9.250 1.2941 0.02763 0.01907 -0.0521 0.1157 1.0000
9.500 1.3085 0.02903 0.02046 -0.0506 0.0874 1.0000
9.750 1.3216 0.03058 0.02197 -0.0488 0.0680 1.0000
10.000 1.3324 0.03223 0.02358 -0.0469 0.0596 1.0000
10.250 1.3417 0.03392 0.02538 -0.0448 0.0551 1.0000
10.500 1.3462 0.03590 0.02737 -0.0424 0.0524 1.0000
10.750 1.3500 0.03780 0.02941 -0.0397 0.0506 1.0000
11.000 1.3535 0.03979 0.03153 -0.0373 0.0486 1.0000
11.250 1.3562 0.04192 0.03376 -0.0351 0.0467 1.0000
11.500 1.3580 0.04427 0.03616 -0.0333 0.0451 1.0000
11.750 1.3618 0.04696 0.03887 -0.0315 0.0438 1.0000
12.000 1.3699 0.04975 0.04179 -0.0298 0.0431 1.0000
12.250 1.3758 0.05261 0.04491 -0.0284 0.0427 1.0000
12.500 1.3789 0.05579 0.04835 -0.0271 0.0424 1.0000
12.750 1.3782 0.05932 0.05216 -0.0260 0.0422 1.0000
13.000 1.3732 0.06327 0.05639 -0.0253 0.0422 1.0000
13.250 1.3637 0.06765 0.06107 -0.0252 0.0422 1.0000
13.500 1.3507 0.07251 0.06620 -0.0258 0.0422 1.0000
13.750 1.3345 0.07795 0.07191 -0.0272 0.0423 1.0000
14.000 1.3160 0.08400 0.07821 -0.0294 0.0424 1.0000
14.250 1.2957 0.09071 0.08515 -0.0326 0.0426 1.0000
14.500 1.2737 0.09807 0.09272 -0.0364 0.0428 1.0000
14.750 1.2510 0.10604 0.10087 -0.0410 0.0431 1.0000
15.000 1.2261 0.11487 0.10992 -0.0467 0.0435 1.0000
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Polar data table (+)
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