GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.9 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe242-il-1000000-n5.txt Download as CSV file: xf-goe242-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 242 (MVA PR.2) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5768 0.05604 0.05309 -0.1065 0.8252 0.0089
-13.750 -0.5933 0.04910 0.04598 -0.1128 0.8185 0.0089
-13.500 -0.5998 0.04403 0.04076 -0.1177 0.8123 0.0090
-13.250 -0.6006 0.03995 0.03656 -0.1220 0.8057 0.0090
-13.000 -0.5971 0.03664 0.03310 -0.1260 0.7989 0.0091
-12.750 -0.5837 0.03345 0.02979 -0.1314 0.7929 0.0093
-12.500 -0.5641 0.03060 0.02683 -0.1371 0.7859 0.0096
-12.250 -0.5392 0.02833 0.02446 -0.1423 0.7791 0.0099
-12.000 -0.5110 0.02646 0.02250 -0.1471 0.7710 0.0102
-11.750 -0.4808 0.02481 0.02073 -0.1516 0.7623 0.0106
-11.500 -0.4488 0.02331 0.01912 -0.1560 0.7515 0.0110
-11.250 -0.4155 0.02190 0.01758 -0.1604 0.7398 0.0114
-11.000 -0.3812 0.02062 0.01614 -0.1646 0.7260 0.0118
-10.750 -0.3465 0.01956 0.01496 -0.1684 0.7081 0.0123
-10.500 -0.3128 0.01884 0.01412 -0.1713 0.6865 0.0127
-10.250 -0.2791 0.01821 0.01335 -0.1740 0.6660 0.0132
-10.000 -0.2449 0.01756 0.01257 -0.1768 0.6488 0.0138
-9.750 -0.2100 0.01687 0.01174 -0.1797 0.6350 0.0143
-9.500 -0.1746 0.01617 0.01089 -0.1826 0.6239 0.0148
-9.250 -0.1403 0.01570 0.01035 -0.1849 0.6147 0.0153
-9.000 -0.1074 0.01543 0.01002 -0.1866 0.6061 0.0158
-8.750 -0.0746 0.01518 0.00970 -0.1881 0.5990 0.0164
-8.500 -0.0418 0.01489 0.00934 -0.1897 0.5923 0.0170
-8.250 -0.0089 0.01455 0.00890 -0.1913 0.5863 0.0176
-8.000 0.0244 0.01417 0.00843 -0.1929 0.5817 0.0181
-7.750 0.0576 0.01380 0.00799 -0.1945 0.5769 0.0186
-7.500 0.0901 0.01357 0.00772 -0.1958 0.5721 0.0191
-7.250 0.1217 0.01343 0.00753 -0.1969 0.5680 0.0195
-7.000 0.1539 0.01323 0.00729 -0.1980 0.5645 0.0200
-6.750 0.1863 0.01298 0.00700 -0.1992 0.5608 0.0206
-6.500 0.2185 0.01277 0.00671 -0.2004 0.5571 0.0213
-6.250 0.2504 0.01258 0.00646 -0.2014 0.5535 0.0219
-6.000 0.2826 0.01237 0.00619 -0.2025 0.5506 0.0223
-5.750 0.3152 0.01212 0.00589 -0.2037 0.5478 0.0227
-5.500 0.3493 0.01174 0.00548 -0.2054 0.5447 0.0234
-5.250 0.3816 0.01153 0.00524 -0.2066 0.5415 0.0239
-5.000 0.4139 0.01135 0.00501 -0.2077 0.5383 0.0244
-4.500 0.4781 0.01101 0.00460 -0.2098 0.5334 0.0256
-4.250 0.5104 0.01084 0.00439 -0.2109 0.5314 0.0261
-4.000 0.5425 0.01068 0.00419 -0.2119 0.5292 0.0265
-3.750 0.5743 0.01054 0.00401 -0.2128 0.5269 0.0269
-3.500 0.6059 0.01043 0.00386 -0.2137 0.5247 0.0273
-3.250 0.6371 0.01035 0.00374 -0.2145 0.5225 0.0275
-3.000 0.6695 0.01018 0.00352 -0.2156 0.5203 0.0286
-2.750 0.7009 0.01009 0.00339 -0.2164 0.5183 0.0294
-2.500 0.7321 0.01001 0.00330 -0.2172 0.5169 0.0301
-2.250 0.7630 0.00994 0.00322 -0.2178 0.5151 0.0308
-2.000 0.7937 0.00990 0.00315 -0.2185 0.5132 0.0315
-1.750 0.8242 0.00987 0.00310 -0.2191 0.5105 0.0324
-1.500 0.8542 0.00987 0.00307 -0.2196 0.5065 0.0332
-1.250 0.8840 0.00990 0.00305 -0.2200 0.5013 0.0344
-1.000 0.9144 0.00987 0.00301 -0.2206 0.4970 0.0381
-0.750 0.9492 0.00947 0.00291 -0.2226 0.4933 0.1836
-0.500 0.9802 0.00938 0.00290 -0.2234 0.4908 0.2267
-0.250 1.0129 0.00910 0.00290 -0.2249 0.4879 0.3597
0.000 1.0423 0.00915 0.00297 -0.2252 0.4852 0.3839
0.250 1.0717 0.00919 0.00303 -0.2256 0.4827 0.3956
0.500 1.1008 0.00925 0.00310 -0.2259 0.4794 0.4068
0.750 1.1296 0.00933 0.00318 -0.2261 0.4753 0.4151
1.000 1.1581 0.00944 0.00325 -0.2263 0.4715 0.4206
1.250 1.1869 0.00952 0.00333 -0.2265 0.4690 0.4247
1.500 1.2157 0.00958 0.00342 -0.2268 0.4666 0.4316
1.750 1.2444 0.00966 0.00351 -0.2270 0.4636 0.4358
2.000 1.2729 0.00976 0.00359 -0.2272 0.4602 0.4377
2.250 1.3011 0.00986 0.00369 -0.2274 0.4566 0.4401
2.500 1.3292 0.00997 0.00379 -0.2276 0.4531 0.4427
2.750 1.3576 0.01006 0.00390 -0.2277 0.4487 0.4457
3.000 1.3853 0.01018 0.00401 -0.2279 0.4427 0.4485
3.250 1.4128 0.01033 0.00414 -0.2279 0.4368 0.4515
3.500 1.4403 0.01046 0.00426 -0.2280 0.4296 0.4538
3.750 1.4672 0.01064 0.00441 -0.2280 0.4215 0.4557
4.000 1.4936 0.01084 0.00459 -0.2279 0.4097 0.4581
4.250 1.5184 0.01117 0.00483 -0.2275 0.3908 0.4610
4.500 1.5395 0.01179 0.00526 -0.2266 0.3572 0.4640
4.750 1.5599 0.01243 0.00574 -0.2255 0.3297 0.4664
5.000 1.5819 0.01292 0.00614 -0.2247 0.3117 0.4686
5.250 1.6039 0.01338 0.00652 -0.2239 0.2975 0.4706
5.500 1.6254 0.01385 0.00692 -0.2230 0.2838 0.4727
5.750 1.6458 0.01435 0.00735 -0.2220 0.2690 0.4750
6.000 1.6660 0.01483 0.00778 -0.2209 0.2553 0.4773
6.250 1.6858 0.01529 0.00820 -0.2197 0.2436 0.4795
6.500 1.7039 0.01582 0.00867 -0.2183 0.2318 0.4818
6.750 1.7195 0.01640 0.00920 -0.2164 0.2198 0.4840
7.000 1.7321 0.01696 0.00972 -0.2139 0.2098 0.4860
7.250 1.7444 0.01751 0.01026 -0.2114 0.2020 0.4878
7.500 1.7560 0.01825 0.01096 -0.2089 0.1919 0.4898
7.750 1.7666 0.01909 0.01176 -0.2065 0.1796 0.4923
8.000 1.7727 0.02024 0.01283 -0.2035 0.1631 0.4947
8.250 1.7505 0.02327 0.01557 -0.1971 0.1127 0.4963
8.500 1.7348 0.02625 0.01842 -0.1922 0.0755 0.4980
8.750 1.7379 0.02804 0.02020 -0.1898 0.0634 0.5002
9.000 1.7428 0.02975 0.02192 -0.1877 0.0552 0.5023
9.250 1.7456 0.03170 0.02385 -0.1855 0.0460 0.5041
9.500 1.7398 0.03449 0.02657 -0.1828 0.0263 0.5057
9.750 1.7364 0.03715 0.02925 -0.1804 0.0147 0.5076
10.000 1.7411 0.03916 0.03132 -0.1789 0.0127 0.5100
10.250 1.7473 0.04107 0.03330 -0.1775 0.0117 0.5124
10.500 1.7527 0.04310 0.03539 -0.1762 0.0110 0.5150
10.750 1.7569 0.04530 0.03766 -0.1749 0.0103 0.5176
11.000 1.7601 0.04768 0.04012 -0.1736 0.0095 0.5201
11.500 1.7687 0.05241 0.04499 -0.1716 0.0087 0.5254
11.750 1.7716 0.05498 0.04763 -0.1706 0.0083 0.5281
12.000 1.7735 0.05771 0.05043 -0.1696 0.0079 0.5308
12.250 1.7746 0.06058 0.05337 -0.1688 0.0075 0.5334
12.500 1.7750 0.06357 0.05643 -0.1679 0.0071 0.5360
12.750 1.7767 0.06641 0.05935 -0.1671 0.0069 0.5384
13.000 1.7774 0.06937 0.06240 -0.1664 0.0067 0.5412
13.250 1.7774 0.07245 0.06556 -0.1657 0.0065 0.5443
13.500 1.7775 0.07554 0.06872 -0.1651 0.0063 0.5478
13.750 1.7766 0.07879 0.07205 -0.1645 0.0061 0.5512
14.000 1.7749 0.08215 0.07549 -0.1639 0.0059 0.5543
14.250 1.7734 0.08548 0.07890 -0.1634 0.0057 0.5575
14.500 1.7697 0.08915 0.08265 -0.1630 0.0055 0.5609
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