GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Reynolds number: 500,000 Max Cl/Cd: 116.78 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe242-il-500000.txt Download as CSV file: xf-goe242-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.0389 0.09029 0.08753 -0.0896 0.8120 0.0263
-10.250 0.0439 0.08708 0.08429 -0.0906 0.8037 0.0271
-10.000 -0.0416 0.09542 0.09263 -0.0864 0.8325 0.0257
-9.750 -0.0334 0.09269 0.08985 -0.0875 0.8241 0.0263
-9.500 -0.0260 0.08957 0.08671 -0.0892 0.8147 0.0271
-9.250 -0.0215 0.08557 0.08267 -0.0918 0.8059 0.0284
-9.000 -0.0369 0.07397 0.07108 -0.1025 0.7982 0.0296
-8.750 -0.0377 0.06930 0.06639 -0.1044 0.7888 0.0301
-8.500 -0.0257 0.06810 0.06514 -0.1044 0.7766 0.0304
-8.250 -0.0142 0.06631 0.06331 -0.1053 0.7631 0.0308
-8.000 -0.0057 0.06348 0.06043 -0.1073 0.7485 0.0315
-7.750 -0.0019 0.05930 0.05621 -0.1108 0.7331 0.0324
-7.500 0.0349 0.03164 0.02730 -0.1746 0.7197 0.0365
-7.250 0.0579 0.02994 0.02562 -0.1748 0.7025 0.0374
-7.000 0.0884 0.02819 0.02369 -0.1779 0.6863 0.0388
-6.750 0.1348 0.02530 0.02010 -0.1866 0.6724 0.0444
-6.500 0.1786 0.02114 0.01519 -0.1915 0.6617 0.0363
-6.250 0.2093 0.01985 0.01377 -0.1924 0.6519 0.0352
-6.000 0.2427 0.01840 0.01208 -0.1942 0.6438 0.0351
-5.750 0.2765 0.01810 0.01153 -0.1957 0.6362 0.0358
-5.500 0.3079 0.01615 0.00946 -0.1971 0.6302 0.0367
-5.250 0.3391 0.01533 0.00861 -0.1980 0.6244 0.0374
-5.000 0.3705 0.01476 0.00798 -0.1989 0.6191 0.0380
-4.750 0.4020 0.01433 0.00747 -0.1998 0.6143 0.0387
-4.500 0.4341 0.01393 0.00706 -0.2009 0.6098 0.0399
-4.250 0.4664 0.01359 0.00668 -0.2020 0.6053 0.0410
-4.000 0.4991 0.01329 0.00630 -0.2032 0.6012 0.0416
-3.750 0.5320 0.01307 0.00599 -0.2044 0.5975 0.0423
-3.500 0.5651 0.01282 0.00571 -0.2056 0.5943 0.0429
-3.250 0.6007 0.01239 0.00523 -0.2077 0.5910 0.0447
-3.000 0.6345 0.01214 0.00493 -0.2092 0.5878 0.0464
-2.750 0.6671 0.01201 0.00472 -0.2103 0.5848 0.0481
-2.500 0.6990 0.01198 0.00458 -0.2113 0.5818 0.0501
-2.250 0.7307 0.01189 0.00445 -0.2121 0.5794 0.0529
-2.000 0.7630 0.01175 0.00434 -0.2132 0.5766 0.0653
-1.750 0.8048 0.01074 0.00416 -0.2175 0.5737 0.3786
-1.500 0.8341 0.01090 0.00433 -0.2177 0.5712 0.4157
-1.250 0.8631 0.01109 0.00448 -0.2178 0.5689 0.4312
-1.000 0.8920 0.01134 0.00468 -0.2179 0.5664 0.4432
-0.750 0.9208 0.01155 0.00484 -0.2180 0.5634 0.4523
-0.500 0.9494 0.01162 0.00493 -0.2181 0.5593 0.4583
-0.250 0.9777 0.01173 0.00503 -0.2181 0.5545 0.4645
0.000 1.0063 0.01193 0.00511 -0.2182 0.5504 0.4707
0.250 1.0346 0.01208 0.00530 -0.2182 0.5472 0.4761
0.500 1.0629 0.01220 0.00545 -0.2183 0.5442 0.4818
0.750 1.0919 0.01227 0.00550 -0.2185 0.5410 0.4850
1.000 1.1208 0.01236 0.00553 -0.2188 0.5378 0.4876
1.250 1.1494 0.01242 0.00558 -0.2190 0.5347 0.4902
1.500 1.1779 0.01259 0.00573 -0.2192 0.5317 0.4925
1.750 1.2064 0.01264 0.00582 -0.2194 0.5292 0.4951
2.000 1.2349 0.01271 0.00592 -0.2196 0.5265 0.4977
2.250 1.2634 0.01279 0.00600 -0.2198 0.5237 0.5006
2.500 1.2918 0.01290 0.00609 -0.2200 0.5209 0.5037
2.750 1.3200 0.01301 0.00618 -0.2202 0.5181 0.5065
3.000 1.3480 0.01317 0.00636 -0.2204 0.5152 0.5092
3.250 1.3756 0.01322 0.00649 -0.2204 0.5122 0.5120
3.500 1.4033 0.01329 0.00659 -0.2205 0.5086 0.5148
3.750 1.4309 0.01337 0.00669 -0.2206 0.5049 0.5173
4.000 1.4584 0.01352 0.00679 -0.2207 0.5014 0.5198
4.250 1.4858 0.01362 0.00693 -0.2208 0.4979 0.5221
4.500 1.5129 0.01367 0.00707 -0.2207 0.4940 0.5244
4.750 1.5396 0.01375 0.00721 -0.2207 0.4898 0.5270
5.000 1.5660 0.01390 0.00735 -0.2205 0.4856 0.5300
5.250 1.5922 0.01401 0.00752 -0.2204 0.4807 0.5332
5.500 1.6180 0.01409 0.00765 -0.2202 0.4741 0.5361
5.750 1.6428 0.01425 0.00778 -0.2198 0.4676 0.5387
6.000 1.6678 0.01431 0.00794 -0.2194 0.4581 0.5414
6.250 1.6910 0.01448 0.00812 -0.2188 0.4453 0.5442
6.500 1.7131 0.01471 0.00834 -0.2179 0.4294 0.5474
6.750 1.7329 0.01507 0.00864 -0.2167 0.4086 0.5505
7.000 1.7489 0.01565 0.00909 -0.2148 0.3817 0.5535
7.250 1.7595 0.01648 0.00977 -0.2121 0.3535 0.5564
8.000 1.7801 0.01916 0.01222 -0.2022 0.3024 0.5654
8.250 1.7905 0.02004 0.01309 -0.1998 0.2909 0.5686
8.500 1.7999 0.02101 0.01405 -0.1974 0.2804 0.5716
8.750 1.8089 0.02205 0.01509 -0.1950 0.2704 0.5747
9.000 1.8197 0.02304 0.01610 -0.1930 0.2611 0.5781
9.250 1.8267 0.02432 0.01737 -0.1907 0.2519 0.5818
9.500 1.8360 0.02551 0.01858 -0.1887 0.2425 0.5856
9.750 1.8426 0.02693 0.02002 -0.1866 0.2321 0.5892
10.000 1.8465 0.02863 0.02171 -0.1843 0.2225 0.5930
10.250 1.8507 0.03037 0.02345 -0.1822 0.2109 0.5970
10.500 1.8521 0.03241 0.02546 -0.1800 0.1976 0.6009
10.750 1.8480 0.03501 0.02802 -0.1775 0.1811 0.6041
11.000 1.8383 0.03822 0.03115 -0.1749 0.1579 0.6073
11.250 1.8091 0.04347 0.03618 -0.1712 0.1191 0.6093
11.500 1.7800 0.04909 0.04169 -0.1682 0.0869 0.6113
11.750 1.7617 0.05391 0.04649 -0.1662 0.0704 0.6141
12.000 1.7509 0.05805 0.05064 -0.1647 0.0591 0.6175
12.250 1.7435 0.06190 0.05453 -0.1635 0.0495 0.6211
12.500 1.7327 0.06624 0.05886 -0.1624 0.0342 0.6248
12.750 1.7164 0.07133 0.06390 -0.1613 0.0209 0.6282
13.000 1.7107 0.07518 0.06783 -0.1605 0.0187 0.6331
13.250 1.7060 0.07898 0.07175 -0.1599 0.0176 0.6376
13.500 1.7014 0.08281 0.07570 -0.1594 0.0168 0.6429
14.000 1.6933 0.09040 0.08353 -0.1586 0.0156 0.6544
14.250 1.6893 0.09426 0.08752 -0.1583 0.0152 0.6612
14.500 1.6846 0.09825 0.09164 -0.1582 0.0148 0.6683
14.750 1.6786 0.10249 0.09601 -0.1582 0.0144 0.6766
15.000 1.6716 0.10691 0.10056 -0.1583 0.0141 0.6858
15.250 1.6631 0.11159 0.10538 -0.1585 0.0138 0.6972
15.500 1.6536 0.11652 0.11046 -0.1590 0.0135 0.7124
15.750 1.6431 0.12173 0.11583 -0.1598 0.0133 0.7378
16.000 1.6295 0.12678 0.12121 -0.1602 0.0131 1.0000
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