GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il) Reynolds number: 200,000 Max Cl/Cd: 77.01 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe234-il-200000.txt Download as CSV file: xf-goe234-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 234 (MVA CA5) 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
------ -------- --------- --------- -------- -------- --------
-9.250 0.0217 0.09789 0.09414 -0.1055 0.9510 0.0735
-9.000 0.0102 0.09464 0.09091 -0.1147 0.9408 0.0790
-8.750 0.0340 0.09052 0.08677 -0.1142 0.9391 0.0804
-8.500 0.0501 0.08881 0.08506 -0.1127 0.9322 0.0819
-8.250 0.0660 0.08663 0.08286 -0.1134 0.9267 0.0845
-8.000 0.0381 0.08397 0.08024 -0.1208 0.9120 0.0911
-7.750 0.0676 0.08070 0.07695 -0.1181 0.9104 0.0927
-7.500 0.0923 0.07914 0.07536 -0.1170 0.9073 0.0957
-7.250 0.0875 0.03770 0.03299 -0.1944 0.8899 0.0680
-7.000 0.1449 0.03117 0.02598 -0.2105 0.8848 0.0670
-6.750 0.2024 0.02804 0.02224 -0.2218 0.8805 0.0680
-6.500 0.2443 0.02558 0.01947 -0.2266 0.8768 0.0685
-6.250 0.2803 0.02353 0.01727 -0.2289 0.8738 0.0694
-6.000 0.3099 0.02245 0.01617 -0.2297 0.8677 0.0709
-5.750 0.3412 0.02159 0.01527 -0.2306 0.8621 0.0732
-5.500 0.3739 0.02078 0.01437 -0.2314 0.8580 0.0753
-5.250 0.4048 0.02022 0.01375 -0.2318 0.8526 0.0770
-5.000 0.4346 0.01984 0.01330 -0.2320 0.8459 0.0787
-4.750 0.4608 0.01971 0.01326 -0.2305 0.8411 0.0820
-4.500 0.4885 0.01974 0.01336 -0.2298 0.8354 0.0862
-4.250 0.5160 0.01984 0.01347 -0.2291 0.8282 0.0901
-4.000 0.5456 0.01995 0.01364 -0.2286 0.8231 0.0965
-3.750 0.5871 0.01905 0.01278 -0.2328 0.8171 0.1137
-3.500 0.6247 0.01861 0.01294 -0.2358 0.8102 0.2362
-3.250 0.6522 0.01918 0.01338 -0.2347 0.8048 0.2685
-3.000 0.6674 0.02079 0.01509 -0.2301 0.7971 0.2730
-2.750 0.6927 0.02144 0.01566 -0.2288 0.7904 0.2835
-2.500 0.7120 0.02249 0.01669 -0.2252 0.7855 0.2861
-2.250 0.7420 0.02262 0.01675 -0.2260 0.7774 0.2978
-2.000 0.7610 0.02338 0.01753 -0.2227 0.7712 0.2997
-1.750 0.7825 0.02395 0.01808 -0.2203 0.7657 0.3035
-1.500 0.8121 0.02402 0.01811 -0.2210 0.7581 0.3146
-1.250 0.8470 0.02409 0.01802 -0.2227 0.7525 0.3283
-1.000 0.8641 0.02444 0.01845 -0.2194 0.7464 0.3306
-0.750 0.8931 0.02486 0.01881 -0.2196 0.7392 0.3445
-0.500 0.9039 0.02512 0.01917 -0.2142 0.7339 0.3498
0.000 0.9422 0.02551 0.01961 -0.2091 0.7189 0.3843
0.250 0.9784 0.02510 0.01910 -0.2115 0.7110 0.3967
0.500 1.0037 0.02453 0.01850 -0.2109 0.7020 0.4016
0.750 1.0400 0.02416 0.01801 -0.2133 0.6928 0.4122
1.000 1.0663 0.02365 0.01746 -0.2130 0.6847 0.4164
1.250 1.1025 0.02349 0.01720 -0.2153 0.6782 0.4275
1.500 1.1277 0.02310 0.01684 -0.2149 0.6709 0.4316
1.750 1.1616 0.02293 0.01655 -0.2165 0.6649 0.4437
2.000 1.1867 0.02267 0.01635 -0.2162 0.6573 0.4495
2.250 1.2203 0.02253 0.01613 -0.2178 0.6501 0.4593
2.500 1.2475 0.02226 0.01585 -0.2178 0.6431 0.4639
2.750 1.2796 0.02225 0.01580 -0.2192 0.6349 0.4744
3.000 1.3081 0.02194 0.01544 -0.2195 0.6283 0.4779
3.250 1.3380 0.02206 0.01558 -0.2203 0.6198 0.4896
3.500 1.3664 0.02173 0.01519 -0.2206 0.6130 0.4931
3.750 1.3941 0.02182 0.01533 -0.2209 0.6045 0.5058
4.000 1.4211 0.02158 0.01507 -0.2209 0.5969 0.5111
4.250 1.4476 0.02156 0.01509 -0.2209 0.5884 0.5240
4.500 1.4750 0.02153 0.01504 -0.2210 0.5800 0.5382
4.750 1.5003 0.02152 0.01508 -0.2207 0.5710 0.5532
5.000 1.5262 0.02142 0.01496 -0.2205 0.5620 0.5618
5.250 1.5649 0.02184 0.01526 -0.2237 0.5510 0.5025
5.500 1.5888 0.02176 0.01517 -0.2230 0.5415 0.5163
5.750 1.6335 0.02145 0.01452 -0.2278 0.5284 0.4218
6.000 1.6556 0.02158 0.01466 -0.2269 0.5153 0.4224
6.250 1.6764 0.02177 0.01481 -0.2256 0.5005 0.4232
6.500 1.6951 0.02202 0.01501 -0.2241 0.4843 0.4243
6.750 1.7114 0.02235 0.01528 -0.2220 0.4669 0.4259
7.000 1.7245 0.02274 0.01568 -0.2195 0.4493 0.4278
7.250 1.7356 0.02326 0.01617 -0.2165 0.4317 0.4298
7.500 1.7433 0.02389 0.01674 -0.2130 0.4148 0.4316
7.750 1.7463 0.02461 0.01740 -0.2087 0.3996 0.4328
8.000 1.7541 0.02547 0.01819 -0.2056 0.3848 0.4341
8.250 1.7628 0.02642 0.01905 -0.2027 0.3717 0.4356
8.500 1.7732 0.02734 0.01995 -0.2003 0.3596 0.4372
8.750 1.7845 0.02829 0.02087 -0.1980 0.3494 0.4390
9.000 1.7945 0.02936 0.02185 -0.1956 0.3402 0.4406
9.250 1.8063 0.03027 0.02284 -0.1936 0.3314 0.4426
9.500 1.8160 0.03135 0.02390 -0.1913 0.3236 0.4448
9.750 1.8266 0.03238 0.02502 -0.1892 0.3156 0.4474
10.000 1.8348 0.03361 0.02622 -0.1869 0.3075 0.4498
10.250 1.8445 0.03477 0.02747 -0.1848 0.3000 0.4521
10.500 1.8531 0.03605 0.02877 -0.1828 0.2929 0.4541
10.750 1.8620 0.03736 0.03011 -0.1808 0.2863 0.4560
11.000 1.8699 0.03873 0.03158 -0.1788 0.2790 0.4578
11.250 1.8759 0.04027 0.03311 -0.1767 0.2722 0.4597
11.500 1.8810 0.04191 0.03492 -0.1747 0.2639 0.4617
11.750 1.8835 0.04380 0.03680 -0.1725 0.2563 0.4640
12.000 1.8886 0.04559 0.03877 -0.1708 0.2480 0.4668
12.250 1.8882 0.04787 0.04102 -0.1686 0.2399 0.4693
12.500 1.8884 0.05027 0.04355 -0.1668 0.2282 0.4717
12.750 1.8865 0.05299 0.04634 -0.1650 0.2153 0.4736
13.000 1.8829 0.05600 0.04941 -0.1633 0.2003 0.4754
13.250 1.8745 0.05971 0.05311 -0.1616 0.1782 0.4769
13.500 1.8527 0.06507 0.05824 -0.1597 0.1332 0.4776
13.750 1.8240 0.07147 0.06439 -0.1579 0.1041 0.4780
14.000 1.8014 0.07735 0.07020 -0.1565 0.0833 0.4787
14.250 1.7829 0.08293 0.07575 -0.1556 0.0686 0.4797
14.500 1.7682 0.08817 0.08101 -0.1550 0.0606 0.4809
14.750 1.7559 0.09324 0.08615 -0.1547 0.0562 0.4823
15.000 1.7442 0.09831 0.09130 -0.1546 0.0533 0.4838
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