GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il) Reynolds number: 500,000 Max Cl/Cd: 120.74 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe233-il-500000.txt Download as CSV file: xf-goe233-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 233 (MVA CA4) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.0421 0.09284 0.09049 -0.0791 0.9333 0.0316
-10.000 -0.0545 0.08687 0.08450 -0.0829 0.9250 0.0343
-9.750 -0.0510 0.08306 0.08068 -0.0830 0.9175 0.0347
-9.500 -0.0401 0.08121 0.07880 -0.0824 0.9094 0.0352
-9.250 -0.0294 0.07928 0.07684 -0.0822 0.9020 0.0358
-9.000 -0.0211 0.07686 0.07440 -0.0824 0.8937 0.0366
-8.750 -0.0156 0.07386 0.07136 -0.0832 0.8863 0.0380
-8.500 -0.0280 0.06671 0.06420 -0.0875 0.8778 0.0409
-8.250 -0.0143 0.06545 0.06290 -0.0867 0.8706 0.0416
-8.000 -0.0014 0.06382 0.06126 -0.0867 0.8627 0.0426
-7.750 0.0063 0.06116 0.05854 -0.0876 0.8556 0.0447
-7.500 0.0059 0.02172 0.01735 -0.1911 0.8682 0.0349
-7.250 0.0417 0.01977 0.01513 -0.1947 0.8616 0.0349
-7.000 0.0739 0.01810 0.01329 -0.1969 0.8559 0.0355
-6.750 0.1064 0.01689 0.01194 -0.1987 0.8493 0.0357
-6.500 0.1380 0.01591 0.01081 -0.1999 0.8427 0.0358
-6.250 0.1692 0.01510 0.00987 -0.2009 0.8363 0.0360
-6.000 0.2003 0.01439 0.00909 -0.2018 0.8290 0.0364
-5.750 0.2311 0.01382 0.00841 -0.2025 0.8227 0.0368
-5.500 0.2622 0.01330 0.00783 -0.2034 0.8154 0.0376
-5.250 0.2931 0.01285 0.00729 -0.2040 0.8082 0.0382
-5.000 0.3243 0.01243 0.00680 -0.2047 0.8004 0.0386
-4.750 0.3553 0.01205 0.00632 -0.2054 0.7918 0.0391
-4.500 0.3865 0.01169 0.00588 -0.2061 0.7834 0.0395
-4.250 0.4176 0.01135 0.00545 -0.2068 0.7751 0.0400
-4.000 0.4489 0.01104 0.00504 -0.2076 0.7676 0.0405
-3.750 0.4807 0.01062 0.00453 -0.2085 0.7596 0.0419
-3.500 0.5117 0.01034 0.00414 -0.2091 0.7524 0.0437
-3.250 0.5422 0.01012 0.00384 -0.2096 0.7446 0.0454
-3.000 0.5723 0.00997 0.00360 -0.2099 0.7376 0.0482
-2.750 0.6030 0.00971 0.00339 -0.2105 0.7297 0.0677
-2.500 0.6331 0.00953 0.00318 -0.2109 0.7227 0.0914
-2.250 0.6639 0.00922 0.00301 -0.2116 0.7156 0.1495
-2.000 0.6936 0.00906 0.00287 -0.2120 0.7088 0.1810
-1.750 0.7232 0.00893 0.00287 -0.2123 0.7026 0.2388
-1.500 0.7519 0.00898 0.00293 -0.2123 0.6952 0.2644
-1.250 0.7803 0.00910 0.00298 -0.2121 0.6880 0.2792
-1.000 0.8087 0.00920 0.00309 -0.2120 0.6799 0.2896
-0.750 0.8369 0.00935 0.00315 -0.2118 0.6731 0.2990
-0.500 0.8652 0.00951 0.00332 -0.2116 0.6669 0.3065
-0.250 0.8935 0.00966 0.00341 -0.2115 0.6606 0.3135
0.000 0.9212 0.00988 0.00363 -0.2112 0.6545 0.3191
0.250 0.9493 0.01006 0.00381 -0.2110 0.6474 0.3258
0.500 0.9771 0.01022 0.00391 -0.2108 0.6406 0.3308
0.750 1.0050 0.01037 0.00409 -0.2105 0.6345 0.3342
1.000 1.0330 0.01049 0.00421 -0.2104 0.6284 0.3375
1.250 1.0609 0.01064 0.00430 -0.2102 0.6227 0.3413
1.500 1.0892 0.01072 0.00437 -0.2101 0.6167 0.3444
1.750 1.1170 0.01078 0.00444 -0.2100 0.6100 0.3476
2.000 1.1444 0.01095 0.00460 -0.2097 0.6037 0.3505
2.250 1.1721 0.01102 0.00472 -0.2096 0.5965 0.3535
2.500 1.1995 0.01115 0.00479 -0.2094 0.5893 0.3561
2.750 1.2273 0.01120 0.00487 -0.2092 0.5819 0.3589
3.000 1.2547 0.01132 0.00495 -0.2090 0.5747 0.3622
3.250 1.2818 0.01140 0.00508 -0.2088 0.5675 0.3651
3.500 1.3088 0.01150 0.00520 -0.2085 0.5588 0.3675
3.750 1.3359 0.01160 0.00531 -0.2083 0.5507 0.3697
4.000 1.3628 0.01170 0.00541 -0.2080 0.5422 0.3720
4.250 1.3896 0.01181 0.00553 -0.2078 0.5339 0.3743
4.500 1.4160 0.01195 0.00564 -0.2074 0.5244 0.3764
4.750 1.4426 0.01204 0.00576 -0.2071 0.5145 0.3784
5.000 1.4683 0.01219 0.00592 -0.2067 0.5046 0.3804
5.250 1.4936 0.01237 0.00610 -0.2062 0.4920 0.3827
5.500 1.5185 0.01259 0.00632 -0.2056 0.4779 0.3852
5.750 1.5430 0.01283 0.00654 -0.2049 0.4639 0.3878
6.000 1.5669 0.01312 0.00679 -0.2042 0.4492 0.3902
6.250 1.5901 0.01345 0.00707 -0.2033 0.4328 0.3923
6.500 1.6121 0.01382 0.00739 -0.2023 0.4130 0.3944
6.750 1.6328 0.01428 0.00777 -0.2010 0.3896 0.3965
7.000 1.6528 0.01478 0.00820 -0.1997 0.3630 0.3987
7.250 1.6703 0.01544 0.00872 -0.1980 0.3299 0.4011
7.500 1.6839 0.01634 0.00939 -0.1957 0.2903 0.4037
7.750 1.6968 0.01724 0.01012 -0.1932 0.2636 0.4062
8.000 1.7110 0.01800 0.01080 -0.1910 0.2469 0.4082
8.500 1.7362 0.01927 0.01207 -0.1858 0.2244 0.4125
8.750 1.7478 0.01997 0.01277 -0.1832 0.2149 0.4147
9.000 1.7599 0.02074 0.01354 -0.1807 0.2047 0.4171
9.250 1.7737 0.02143 0.01426 -0.1787 0.1941 0.4197
9.500 1.7851 0.02230 0.01513 -0.1763 0.1807 0.4222
9.750 1.7920 0.02351 0.01622 -0.1735 0.1571 0.4245
10.000 1.7842 0.02578 0.01818 -0.1691 0.1089 0.4264
10.250 1.7727 0.02853 0.02071 -0.1646 0.0764 0.4279
10.500 1.7702 0.03074 0.02287 -0.1614 0.0616 0.4299
10.750 1.7722 0.03269 0.02482 -0.1589 0.0538 0.4321
11.000 1.7743 0.03470 0.02686 -0.1565 0.0487 0.4345
11.250 1.7788 0.03656 0.02878 -0.1544 0.0453 0.4369
11.500 1.7788 0.03889 0.03114 -0.1522 0.0422 0.4388
11.750 1.7836 0.04083 0.03319 -0.1504 0.0401 0.4415
12.000 1.7873 0.04291 0.03537 -0.1487 0.0382 0.4441
12.250 1.7873 0.04541 0.03794 -0.1469 0.0365 0.4468
12.500 1.7812 0.04864 0.04126 -0.1449 0.0347 0.4492
12.750 1.7858 0.05083 0.04355 -0.1437 0.0335 0.4527
13.000 1.7880 0.05334 0.04616 -0.1424 0.0322 0.4561
13.250 1.7883 0.05612 0.04904 -0.1412 0.0309 0.4594
13.500 1.7843 0.05948 0.05248 -0.1400 0.0298 0.4625
13.750 1.7731 0.06383 0.05693 -0.1388 0.0287 0.4650
14.000 1.7759 0.06652 0.05975 -0.1380 0.0280 0.4691
14.250 1.7755 0.06966 0.06301 -0.1373 0.0271 0.4732
14.500 1.7740 0.07300 0.06646 -0.1367 0.0263 0.4778
14.750 1.7715 0.07651 0.07007 -0.1362 0.0255 0.4830
15.000 1.7663 0.08043 0.07408 -0.1358 0.0248 0.4882
15.250 1.7555 0.08515 0.07890 -0.1355 0.0241 0.4936
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