GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il) Reynolds number: 100,000 Max Cl/Cd: 60.34 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe144-il-100000-n5.txt Download as CSV file: xf-goe144-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 144 (MVA H.21) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3418 0.09311 0.08847 -0.0279 1.0000 0.0311
-7.500 -0.3465 0.09065 0.08610 -0.0268 1.0000 0.0310
-7.250 -0.3490 0.08789 0.08342 -0.0264 1.0000 0.0309
-7.000 -0.3499 0.08514 0.08073 -0.0259 1.0000 0.0305
-6.750 -0.3511 0.08231 0.07796 -0.0259 1.0000 0.0303
-6.500 -0.3516 0.07921 0.07492 -0.0265 1.0000 0.0301
-6.250 -0.3501 0.07594 0.07169 -0.0275 1.0000 0.0300
-6.000 -0.3464 0.07231 0.06808 -0.0291 1.0000 0.0300
-5.750 -0.3398 0.06839 0.06417 -0.0313 1.0000 0.0299
-5.500 -0.3090 0.06091 0.05656 -0.0416 0.9958 0.0312
-5.250 -0.2765 0.05693 0.05248 -0.0477 0.9897 0.0338
-5.000 -0.2380 0.05092 0.04627 -0.0561 0.9835 0.0349
-4.750 -0.1958 0.04451 0.03957 -0.0647 0.9774 0.0377
-4.500 -0.1489 0.02907 0.02281 -0.0772 0.9723 0.0419
-4.250 -0.1118 0.02777 0.02134 -0.0799 0.9662 0.0459
-4.000 -0.0770 0.02422 0.01701 -0.0824 0.9590 0.0515
-3.750 -0.0385 0.02279 0.01527 -0.0849 0.9532 0.0563
-3.500 -0.0052 0.02128 0.01327 -0.0860 0.9444 0.0622
-3.250 0.0338 0.01989 0.01159 -0.0883 0.9386 0.0671
-3.000 0.0674 0.01880 0.01019 -0.0892 0.9293 0.0747
-2.750 0.1054 0.01795 0.00923 -0.0911 0.9222 0.0850
-2.500 0.1414 0.01764 0.00886 -0.0926 0.9128 0.0998
-2.250 0.1763 0.01744 0.00858 -0.0937 0.9022 0.1117
-2.000 0.2122 0.01718 0.00819 -0.0950 0.8916 0.1217
-1.750 0.2469 0.01695 0.00785 -0.0961 0.8796 0.1326
-1.500 0.2780 0.01678 0.00759 -0.0964 0.8639 0.1444
-1.250 0.3079 0.01639 0.00709 -0.0965 0.8463 0.1515
-1.000 0.3385 0.01594 0.00658 -0.0967 0.8280 0.1576
-0.750 0.3690 0.01556 0.00615 -0.0969 0.8078 0.1655
-0.500 0.4006 0.01520 0.00573 -0.0972 0.7871 0.1745
0.000 0.4648 0.01474 0.00506 -0.0980 0.7476 0.1984
0.250 0.4955 0.01464 0.00488 -0.0982 0.7289 0.2114
0.500 0.5255 0.01461 0.00476 -0.0984 0.7114 0.2246
0.750 0.5544 0.01463 0.00471 -0.0983 0.6950 0.2389
1.000 0.5824 0.01468 0.00469 -0.0981 0.6792 0.2546
1.250 0.6095 0.01473 0.00471 -0.0978 0.6636 0.2736
1.500 0.6357 0.01475 0.00474 -0.0973 0.6461 0.3002
1.750 0.6614 0.01460 0.00477 -0.0969 0.6290 0.3610
2.000 0.6956 0.01355 0.00481 -0.0979 0.6120 1.0000
2.250 0.7212 0.01378 0.00491 -0.0973 0.5977 1.0000
2.500 0.7469 0.01401 0.00504 -0.0967 0.5852 1.0000
2.750 0.7725 0.01425 0.00519 -0.0961 0.5733 1.0000
3.000 0.7980 0.01450 0.00538 -0.0954 0.5616 1.0000
3.250 0.8232 0.01474 0.00560 -0.0948 0.5498 1.0000
3.500 0.8484 0.01500 0.00584 -0.0942 0.5380 1.0000
3.750 0.8735 0.01527 0.00608 -0.0935 0.5266 1.0000
4.000 0.8982 0.01554 0.00636 -0.0928 0.5143 1.0000
4.250 0.9227 0.01582 0.00662 -0.0920 0.5014 1.0000
4.500 0.9465 0.01609 0.00690 -0.0912 0.4866 1.0000
4.750 0.9699 0.01637 0.00722 -0.0902 0.4699 1.0000
5.000 0.9931 0.01665 0.00753 -0.0892 0.4527 1.0000
5.250 1.0162 0.01695 0.00787 -0.0883 0.4360 1.0000
5.500 1.0392 0.01726 0.00824 -0.0873 0.4195 1.0000
5.750 1.0618 0.01760 0.00864 -0.0862 0.4023 1.0000
6.000 1.0837 0.01796 0.00903 -0.0851 0.3828 1.0000
6.250 1.1031 0.01836 0.00939 -0.0836 0.3490 1.0000
6.500 1.1208 0.01893 0.00978 -0.0818 0.3066 1.0000
6.750 1.1388 0.01960 0.01032 -0.0803 0.2713 1.0000
7.000 1.1562 0.02039 0.01101 -0.0787 0.2373 1.0000
7.250 1.1710 0.02144 0.01181 -0.0769 0.1850 1.0000
7.500 1.1843 0.02269 0.01274 -0.0749 0.1288 1.0000
7.750 1.1939 0.02435 0.01402 -0.0725 0.0820 1.0000
8.000 1.1998 0.02633 0.01559 -0.0696 0.0317 1.0000
8.250 1.2123 0.02760 0.01700 -0.0674 0.0277 1.0000
8.500 1.2229 0.02898 0.01854 -0.0649 0.0253 1.0000
8.750 1.2300 0.03056 0.02028 -0.0621 0.0234 1.0000
9.000 1.2384 0.03180 0.02173 -0.0595 0.0221 1.0000
9.250 1.2437 0.03320 0.02341 -0.0565 0.0209 1.0000
9.500 1.2469 0.03478 0.02518 -0.0536 0.0202 1.0000
9.750 1.2481 0.03654 0.02713 -0.0507 0.0197 1.0000
10.000 1.2482 0.03846 0.02923 -0.0481 0.0193 1.0000
10.250 1.2470 0.04062 0.03156 -0.0458 0.0188 1.0000
10.500 1.2456 0.04295 0.03405 -0.0438 0.0185 1.0000
10.750 1.2447 0.04541 0.03666 -0.0422 0.0181 1.0000
11.000 1.2438 0.04805 0.03943 -0.0409 0.0174 1.0000
11.250 1.2437 0.05078 0.04228 -0.0399 0.0169 1.0000
11.500 1.2438 0.05365 0.04526 -0.0391 0.0162 1.0000
11.750 1.2445 0.05665 0.04836 -0.0383 0.0155 1.0000
12.000 1.2482 0.05959 0.05140 -0.0373 0.0150 1.0000
12.250 1.2543 0.06249 0.05443 -0.0364 0.0147 1.0000
12.500 1.2602 0.06572 0.05783 -0.0355 0.0145 1.0000
12.750 1.2631 0.06927 0.06158 -0.0350 0.0143 1.0000
13.000 1.2622 0.07324 0.06577 -0.0349 0.0142 1.0000
13.250 1.2580 0.07756 0.07040 -0.0353 0.0141 1.0000
13.500 1.2514 0.08207 0.07516 -0.0361 0.0141 1.0000
13.750 1.2426 0.08694 0.08025 -0.0375 0.0141 1.0000
14.000 1.2317 0.09223 0.08577 -0.0393 0.0141 1.0000
14.250 1.2205 0.09764 0.09140 -0.0417 0.0141 1.0000
14.500 1.2083 0.10344 0.09741 -0.0445 0.0141 1.0000
14.750 1.1960 0.10952 0.10370 -0.0478 0.0142 1.0000
15.000 1.1835 0.11593 0.11030 -0.0515 0.0142 1.0000
15.250 1.1709 0.12270 0.11726 -0.0557 0.0143 1.0000
15.500 1.1581 0.12993 0.12467 -0.0604 0.0144 1.0000
15.750 1.1459 0.13753 0.13243 -0.0655 0.0145 1.0000
16.000 1.1324 0.14602 0.14108 -0.0713 0.0146 1.0000
16.250 1.1187 0.15530 0.15051 -0.0776 0.0148 1.0000
16.500 1.1030 0.16617 0.16146 -0.0849 0.0151 1.0000
16.750 1.0849 0.17941 0.17480 -0.0931 0.0157 1.0000
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Polar data table (+)
Polar graphs
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