GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Reynolds number: 500,000 Max Cl/Cd: 114.64 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe242-il-500000-n5.txt Download as CSV file: xf-goe242-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.0846 0.09083 0.08757 -0.0868 0.7534 0.0121
-10.250 -0.0783 0.08760 0.08430 -0.0887 0.7420 0.0123
-10.000 -0.2075 0.05093 0.04762 -0.1147 0.7488 0.0137
-9.750 -0.2434 0.02755 0.02313 -0.1549 0.7382 0.0150
-9.500 -0.2103 0.02662 0.02210 -0.1590 0.7236 0.0153
-9.250 -0.1761 0.02573 0.02107 -0.1632 0.7066 0.0156
-9.000 -0.1406 0.02465 0.01981 -0.1679 0.6884 0.0160
-8.750 -0.1034 0.02311 0.01798 -0.1733 0.6713 0.0167
-8.500 -0.0656 0.02074 0.01514 -0.1788 0.6570 0.0181
-8.250 -0.0316 0.01979 0.01397 -0.1818 0.6450 0.0187
-8.000 0.0010 0.01945 0.01352 -0.1838 0.6345 0.0191
-7.750 0.0338 0.01908 0.01304 -0.1857 0.6252 0.0197
-7.500 0.0665 0.01855 0.01236 -0.1876 0.6173 0.0205
-7.250 0.0996 0.01785 0.01148 -0.1895 0.6101 0.0214
-7.000 0.1326 0.01729 0.01069 -0.1912 0.6037 0.0223
-6.750 0.1649 0.01666 0.00999 -0.1927 0.5986 0.0231
-6.500 0.1969 0.01627 0.00954 -0.1941 0.5935 0.0237
-6.250 0.2288 0.01589 0.00909 -0.1953 0.5887 0.0244
-6.000 0.2608 0.01550 0.00861 -0.1966 0.5846 0.0252
-5.750 0.2931 0.01515 0.00819 -0.1978 0.5807 0.0261
-5.500 0.3251 0.01484 0.00779 -0.1989 0.5767 0.0269
-5.250 0.3570 0.01458 0.00744 -0.2000 0.5730 0.0274
-5.000 0.3902 0.01408 0.00688 -0.2015 0.5696 0.0281
-4.750 0.4236 0.01369 0.00648 -0.2030 0.5666 0.0291
-4.500 0.4566 0.01340 0.00617 -0.2044 0.5634 0.0299
-4.250 0.4896 0.01314 0.00586 -0.2058 0.5600 0.0306
-4.000 0.5225 0.01291 0.00557 -0.2071 0.5568 0.0312
-3.750 0.5551 0.01272 0.00530 -0.2083 0.5539 0.0319
-3.500 0.5875 0.01256 0.00508 -0.2095 0.5514 0.0326
-3.250 0.6197 0.01240 0.00489 -0.2105 0.5492 0.0334
-3.000 0.6523 0.01222 0.00467 -0.2117 0.5468 0.0342
-2.750 0.6848 0.01205 0.00444 -0.2129 0.5444 0.0352
-2.500 0.7165 0.01195 0.00429 -0.2138 0.5421 0.0363
-2.250 0.7475 0.01189 0.00418 -0.2146 0.5399 0.0375
-2.000 0.7782 0.01186 0.00410 -0.2153 0.5378 0.0390
-1.750 0.8086 0.01187 0.00405 -0.2159 0.5357 0.0409
-1.500 0.8394 0.01182 0.00400 -0.2166 0.5337 0.0470
-1.250 0.8764 0.01126 0.00384 -0.2192 0.5316 0.2118
-1.000 0.9106 0.01089 0.00382 -0.2211 0.5294 0.3532
-0.750 0.9400 0.01095 0.00392 -0.2215 0.5265 0.3895
-0.500 0.9687 0.01105 0.00399 -0.2217 0.5222 0.4041
-0.250 0.9972 0.01118 0.00408 -0.2218 0.5174 0.4151
0.000 1.0261 0.01125 0.00415 -0.2221 0.5129 0.4251
0.250 1.0546 0.01135 0.00425 -0.2222 0.5090 0.4342
0.500 1.0831 0.01147 0.00430 -0.2224 0.5056 0.4383
0.750 1.1112 0.01160 0.00443 -0.2225 0.5027 0.4438
1.000 1.1397 0.01171 0.00454 -0.2226 0.5002 0.4503
1.250 1.1684 0.01179 0.00462 -0.2228 0.4969 0.4538
1.500 1.1967 0.01188 0.00471 -0.2230 0.4932 0.4564
1.750 1.2247 0.01199 0.00482 -0.2231 0.4899 0.4590
2.000 1.2524 0.01213 0.00494 -0.2232 0.4867 0.4617
2.250 1.2805 0.01222 0.00505 -0.2233 0.4839 0.4640
2.500 1.3086 0.01232 0.00517 -0.2235 0.4809 0.4668
2.750 1.3365 0.01243 0.00529 -0.2236 0.4776 0.4696
3.000 1.3640 0.01256 0.00541 -0.2237 0.4741 0.4722
3.250 1.3909 0.01270 0.00557 -0.2236 0.4707 0.4748
3.500 1.4185 0.01281 0.00573 -0.2237 0.4672 0.4776
3.750 1.4458 0.01293 0.00588 -0.2238 0.4629 0.4802
4.000 1.4724 0.01308 0.00604 -0.2237 0.4579 0.4825
4.250 1.4986 0.01325 0.00621 -0.2235 0.4527 0.4850
4.500 1.5252 0.01338 0.00638 -0.2235 0.4462 0.4876
4.750 1.5503 0.01359 0.00657 -0.2231 0.4390 0.4898
5.000 1.5763 0.01375 0.00678 -0.2230 0.4310 0.4920
5.250 1.6004 0.01399 0.00702 -0.2225 0.4201 0.4943
5.500 1.6225 0.01434 0.00731 -0.2217 0.4012 0.4966
5.750 1.6396 0.01497 0.00779 -0.2200 0.3716 0.4990
6.000 1.6536 0.01577 0.00842 -0.2179 0.3436 0.5013
6.250 1.6673 0.01656 0.00908 -0.2158 0.3218 0.5036
6.500 1.6799 0.01733 0.00976 -0.2134 0.3044 0.5057
6.750 1.6886 0.01805 0.01045 -0.2103 0.2900 0.5079
7.000 1.6990 0.01881 0.01118 -0.2076 0.2776 0.5104
7.250 1.7104 0.01962 0.01197 -0.2053 0.2667 0.5131
7.500 1.7217 0.02048 0.01281 -0.2030 0.2553 0.5158
7.750 1.7332 0.02137 0.01368 -0.2009 0.2451 0.5185
8.000 1.7430 0.02239 0.01469 -0.1987 0.2358 0.5209
8.250 1.7531 0.02344 0.01574 -0.1966 0.2257 0.5233
8.500 1.7623 0.02461 0.01692 -0.1946 0.2165 0.5256
8.750 1.7687 0.02602 0.01831 -0.1923 0.2066 0.5281
9.000 1.7766 0.02738 0.01968 -0.1903 0.1962 0.5309
9.250 1.7794 0.02920 0.02147 -0.1880 0.1821 0.5338
9.500 1.7761 0.03159 0.02377 -0.1852 0.1631 0.5364
9.750 1.7512 0.03598 0.02792 -0.1809 0.1199 0.5380
10.000 1.7249 0.04080 0.03261 -0.1770 0.0831 0.5393
10.250 1.7145 0.04436 0.03618 -0.1747 0.0684 0.5413
10.500 1.7115 0.04733 0.03919 -0.1730 0.0592 0.5437
10.750 1.7100 0.05026 0.04217 -0.1716 0.0512 0.5463
11.000 1.7060 0.05354 0.04547 -0.1702 0.0414 0.5489
11.250 1.6899 0.05831 0.05017 -0.1685 0.0188 0.5508
11.500 1.6856 0.06185 0.05378 -0.1674 0.0153 0.5533
11.750 1.6855 0.06494 0.05697 -0.1666 0.0140 0.5558
12.000 1.6844 0.06818 0.06031 -0.1658 0.0130 0.5585
12.250 1.6838 0.07136 0.06359 -0.1650 0.0122 0.5616
12.500 1.6847 0.07440 0.06673 -0.1644 0.0116 0.5651
12.750 1.6846 0.07759 0.07003 -0.1638 0.0111 0.5687
13.000 1.6841 0.08084 0.07338 -0.1633 0.0107 0.5720
13.250 1.6819 0.08433 0.07699 -0.1628 0.0102 0.5754
13.500 1.6787 0.08800 0.08076 -0.1623 0.0098 0.5789
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