GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Reynolds number: 200,000 Max Cl/Cd: 73.34 at α=0.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe244-il-200000.txt Download as CSV file: xf-goe244-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 244 (MVA PR.4) 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
------ -------- --------- --------- -------- -------- --------
-10.000 0.2901 0.10440 0.10045 -0.1364 0.8906 0.0565
-9.750 0.3002 0.10189 0.09791 -0.1373 0.8862 0.0581
-9.500 0.2893 0.10091 0.09694 -0.1406 0.8780 0.0599
-9.250 0.3001 0.09780 0.09383 -0.1407 0.8721 0.0604
-9.000 0.3205 0.09471 0.09071 -0.1396 0.8682 0.0611
-8.750 0.3329 0.09265 0.08864 -0.1393 0.8622 0.0622
-8.500 0.3421 0.09067 0.08666 -0.1395 0.8550 0.0638
-8.250 0.3454 0.08854 0.08450 -0.1418 0.8498 0.0664
-8.000 0.3383 0.08652 0.08251 -0.1449 0.8415 0.0673
-7.750 0.3581 0.08388 0.07985 -0.1433 0.8363 0.0679
-7.500 0.3758 0.08147 0.07740 -0.1430 0.8319 0.0689
-7.250 0.3875 0.07953 0.07545 -0.1431 0.8258 0.0702
-7.000 0.3954 0.07764 0.07357 -0.1435 0.8181 0.0721
-6.750 0.3797 0.07517 0.07107 -0.1506 0.8113 0.0751
-6.500 0.3950 0.07310 0.06903 -0.1475 0.8042 0.0757
-6.250 0.4129 0.07113 0.06705 -0.1465 0.7987 0.0766
-6.000 0.4289 0.06920 0.06507 -0.1466 0.7944 0.0781
-5.750 0.4379 0.06756 0.06344 -0.1472 0.7883 0.0801
-5.500 0.4403 0.06380 0.05971 -0.1570 0.7800 0.0844
-5.250 0.4599 0.06199 0.05785 -0.1551 0.7759 0.0853
-5.000 0.4761 0.06056 0.05641 -0.1543 0.7704 0.0868
-4.750 0.4885 0.05897 0.05485 -0.1550 0.7630 0.0898
-4.500 0.5148 0.05451 0.05033 -0.1653 0.7576 0.0956
-4.250 0.5339 0.05316 0.04895 -0.1647 0.7523 0.0974
-4.000 0.7133 0.02616 0.02019 -0.2387 0.7460 0.0657
-3.750 0.7586 0.02386 0.01752 -0.2433 0.7406 0.0631
-3.500 0.8067 0.02196 0.01504 -0.2477 0.7360 0.0612
-3.250 0.8330 0.02137 0.01443 -0.2477 0.7276 0.0621
-3.000 0.8675 0.02059 0.01349 -0.2489 0.7209 0.0634
-2.750 0.9006 0.01988 0.01261 -0.2499 0.7140 0.0640
-2.500 0.9299 0.01929 0.01195 -0.2500 0.7054 0.0644
-2.250 0.9650 0.01864 0.01114 -0.2510 0.6988 0.0653
-2.000 0.9906 0.01835 0.01085 -0.2505 0.6891 0.0664
-1.750 1.0236 0.01783 0.01029 -0.2513 0.6811 0.0682
-1.500 1.0502 0.01760 0.01013 -0.2511 0.6706 0.0707
-1.250 1.0830 0.01732 0.00971 -0.2517 0.6615 0.0748
-1.000 1.1096 0.01713 0.00958 -0.2517 0.6490 0.0815
-0.750 1.1409 0.01684 0.00920 -0.2524 0.6368 0.0953
-0.500 1.1760 0.01630 0.00899 -0.2542 0.6233 0.2715
-0.250 1.1986 0.01646 0.00914 -0.2531 0.6074 0.3042
0.000 1.2207 0.01668 0.00928 -0.2519 0.5905 0.3264
0.250 1.2417 0.01693 0.00945 -0.2506 0.5728 0.3453
0.500 1.2618 0.01725 0.00965 -0.2491 0.5545 0.3625
0.750 1.2810 0.01762 0.00991 -0.2474 0.5368 0.3773
1.000 1.2996 0.01805 0.01024 -0.2457 0.5206 0.3929
1.250 1.3179 0.01854 0.01061 -0.2439 0.5065 0.4109
1.500 1.3365 0.01906 0.01099 -0.2422 0.4943 0.4284
1.750 1.3551 0.01953 0.01139 -0.2406 0.4834 0.4452
2.250 1.3930 0.02050 0.01223 -0.2375 0.4664 0.4751
2.500 1.4137 0.02101 0.01263 -0.2363 0.4591 0.4927
2.750 1.4357 0.02151 0.01307 -0.2353 0.4526 0.5105
3.000 1.4562 0.02198 0.01353 -0.2341 0.4464 0.5274
3.250 1.4800 0.02246 0.01391 -0.2335 0.4410 0.5436
3.500 1.5071 0.02292 0.01429 -0.2335 0.4362 0.5571
3.750 1.5272 0.02337 0.01479 -0.2324 0.4318 0.5696
4.000 1.5494 0.02384 0.01523 -0.2316 0.4275 0.5830
4.250 1.5731 0.02427 0.01566 -0.2310 0.4236 0.5944
4.500 1.6033 0.02472 0.01599 -0.2316 0.4199 0.6071
4.750 1.6292 0.02523 0.01648 -0.2315 0.4166 0.6198
5.000 1.6486 0.02570 0.01704 -0.2303 0.4135 0.6296
5.250 1.6705 0.02620 0.01756 -0.2296 0.4103 0.6406
5.500 1.6935 0.02667 0.01805 -0.2291 0.4073 0.6510
5.750 1.7183 0.02713 0.01849 -0.2288 0.4043 0.6622
6.000 1.7495 0.02761 0.01888 -0.2297 0.4013 0.6757
6.250 1.7776 0.02816 0.01944 -0.2300 0.3983 0.6886
6.500 1.7903 0.02875 0.02015 -0.2279 0.3955 0.7004
6.750 1.8058 0.02933 0.02081 -0.2262 0.3924 0.7142
7.000 1.8229 0.02986 0.02140 -0.2248 0.3890 0.7297
7.250 1.8432 0.03032 0.02186 -0.2239 0.3858 0.7465
7.500 1.8704 0.03074 0.02224 -0.2241 0.3827 0.7664
7.750 1.8993 0.03125 0.02277 -0.2247 0.3797 0.7966
8.000 1.9050 0.03177 0.02355 -0.2215 0.3776 1.0000
8.250 1.9180 0.03258 0.02443 -0.2198 0.3752 1.0000
8.500 1.9323 0.03336 0.02525 -0.2183 0.3726 1.0000
8.750 1.9477 0.03407 0.02596 -0.2169 0.3696 1.0000
9.000 1.9671 0.03465 0.02651 -0.2160 0.3666 1.0000
9.250 1.9940 0.03515 0.02692 -0.2163 0.3639 1.0000
9.500 2.0251 0.03581 0.02752 -0.2172 0.3615 1.0000
9.750 2.0262 0.03692 0.02880 -0.2138 0.3595 1.0000
10.000 2.0284 0.03807 0.03010 -0.2108 0.3570 1.0000
10.250 2.0332 0.03917 0.03129 -0.2081 0.3540 1.0000
10.500 2.0432 0.04008 0.03226 -0.2062 0.3511 1.0000
10.750 2.0594 0.04078 0.03296 -0.2050 0.3485 1.0000
11.000 2.0829 0.04124 0.03337 -0.2048 0.3459 1.0000
11.250 2.1104 0.04182 0.03391 -0.2052 0.3431 1.0000
11.500 2.1012 0.04361 0.03591 -0.2011 0.3410 1.0000
11.750 2.0965 0.04536 0.03784 -0.1978 0.3384 1.0000
12.000 2.0965 0.04695 0.03956 -0.1951 0.3357 1.0000
12.250 2.1025 0.04822 0.04091 -0.1931 0.3329 1.0000
12.500 2.1164 0.04898 0.04167 -0.1920 0.3299 1.0000
12.750 2.1442 0.04901 0.04159 -0.1922 0.3266 1.0000
13.000 2.1345 0.05129 0.04406 -0.1889 0.3236 1.0000
13.250 2.1155 0.05426 0.04726 -0.1850 0.3203 1.0000
13.500 2.1080 0.05655 0.04968 -0.1823 0.3165 1.0000
13.750 2.1158 0.05764 0.05077 -0.1809 0.3125 1.0000
14.000 2.1446 0.05721 0.05017 -0.1810 0.3081 1.0000
14.250 2.1121 0.06189 0.05518 -0.1772 0.3047 1.0000
14.500 2.0946 0.06564 0.05913 -0.1748 0.3003 1.0000
14.750 2.0957 0.06766 0.06119 -0.1735 0.2959 1.0000
15.000 2.1191 0.06742 0.06080 -0.1731 0.2915 1.0000
15.250 2.0830 0.07365 0.06736 -0.1706 0.2869 1.0000
15.500 2.0670 0.07797 0.07185 -0.1693 0.2816 1.0000
15.750 2.0750 0.07949 0.07333 -0.1687 0.2767 1.0000
16.000 2.0528 0.08489 0.07893 -0.1677 0.2709 1.0000
16.250 2.0320 0.09036 0.08456 -0.1671 0.2643 1.0000
16.500 2.0417 0.09177 0.08588 -0.1667 0.2587 1.0000
16.750 1.9988 0.10062 0.09504 -0.1667 0.2502 1.0000
17.000 2.0051 0.10257 0.09689 -0.1665 0.2437 1.0000
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