GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Reynolds number: 500,000 Max Cl/Cd: 90.27 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe243-il-500000-n5.txt Download as CSV file: xf-goe243-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 243 (MVA PR.3) 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1745 0.05057 0.04634 -0.1363 0.7836 0.0264
-10.750 -0.1915 0.04401 0.03954 -0.1438 0.7771 0.0264
-10.500 -0.1957 0.03988 0.03527 -0.1485 0.7704 0.0265
-10.250 -0.1900 0.03671 0.03196 -0.1531 0.7643 0.0266
-10.000 -0.1747 0.03387 0.02896 -0.1583 0.7589 0.0267
-9.750 -0.1532 0.03144 0.02643 -0.1634 0.7538 0.0268
-9.500 -0.1276 0.02939 0.02427 -0.1681 0.7481 0.0270
-9.000 -0.0688 0.02606 0.02069 -0.1769 0.7378 0.0273
-8.750 -0.0366 0.02464 0.01918 -0.1810 0.7325 0.0275
-8.500 -0.0038 0.02339 0.01782 -0.1846 0.7253 0.0277
-8.250 0.0292 0.02230 0.01659 -0.1879 0.7178 0.0279
-8.000 0.0629 0.02130 0.01550 -0.1909 0.7110 0.0281
-7.750 0.0967 0.02041 0.01452 -0.1937 0.7048 0.0283
-7.500 0.1303 0.01964 0.01364 -0.1961 0.6992 0.0286
-7.250 0.1641 0.01893 0.01284 -0.1984 0.6940 0.0288
-7.000 0.1979 0.01828 0.01213 -0.2005 0.6885 0.0291
-6.750 0.2316 0.01770 0.01148 -0.2025 0.6828 0.0293
-6.500 0.2651 0.01720 0.01087 -0.2043 0.6771 0.0296
-6.250 0.2992 0.01670 0.01032 -0.2062 0.6717 0.0299
-6.000 0.3333 0.01624 0.00980 -0.2081 0.6660 0.0301
-5.750 0.3674 0.01579 0.00929 -0.2100 0.6601 0.0304
-5.500 0.4023 0.01532 0.00878 -0.2120 0.6544 0.0308
-5.250 0.4377 0.01488 0.00833 -0.2142 0.6482 0.0312
-5.000 0.4725 0.01451 0.00792 -0.2162 0.6417 0.0317
-4.750 0.5069 0.01419 0.00754 -0.2180 0.6358 0.0323
-4.500 0.5415 0.01386 0.00717 -0.2197 0.6298 0.0329
-4.250 0.5754 0.01358 0.00683 -0.2213 0.6225 0.0334
-4.000 0.6086 0.01336 0.00652 -0.2227 0.6156 0.0339
-3.750 0.6422 0.01311 0.00623 -0.2241 0.6085 0.0344
-3.500 0.6755 0.01287 0.00593 -0.2255 0.5992 0.0351
-3.250 0.7076 0.01272 0.00572 -0.2266 0.5901 0.0359
-3.000 0.7391 0.01261 0.00554 -0.2274 0.5799 0.0368
-2.750 0.7701 0.01253 0.00539 -0.2282 0.5715 0.0379
-2.500 0.8012 0.01245 0.00525 -0.2289 0.5624 0.0390
-2.250 0.8314 0.01241 0.00515 -0.2295 0.5530 0.0408
-2.000 0.8613 0.01239 0.00507 -0.2299 0.5417 0.0433
-1.750 0.8906 0.01241 0.00502 -0.2303 0.5296 0.0470
-1.250 0.9480 0.01250 0.00500 -0.2308 0.5028 0.0660
-1.000 0.9765 0.01255 0.00502 -0.2310 0.4921 0.0846
-0.750 1.0061 0.01251 0.00499 -0.2316 0.4814 0.1196
-0.500 1.0386 0.01222 0.00500 -0.2331 0.4716 0.2720
-0.250 1.0654 0.01239 0.00514 -0.2330 0.4613 0.2928
0.000 1.0918 0.01258 0.00528 -0.2327 0.4522 0.3048
0.250 1.1179 0.01278 0.00544 -0.2323 0.4430 0.3177
0.500 1.1436 0.01299 0.00562 -0.2319 0.4353 0.3296
0.750 1.1698 0.01317 0.00578 -0.2316 0.4281 0.3400
1.000 1.1948 0.01340 0.00598 -0.2311 0.4205 0.3483
1.250 1.2200 0.01361 0.00616 -0.2306 0.4141 0.3555
1.500 1.2451 0.01383 0.00634 -0.2301 0.4073 0.3608
1.750 1.2683 0.01412 0.00655 -0.2292 0.3998 0.3644
2.000 1.2926 0.01433 0.00676 -0.2286 0.3929 0.3693
2.250 1.3161 0.01458 0.00699 -0.2278 0.3861 0.3740
2.500 1.3381 0.01487 0.00724 -0.2268 0.3802 0.3787
2.750 1.3596 0.01511 0.00746 -0.2257 0.3758 0.3833
3.000 1.3802 0.01534 0.00770 -0.2243 0.3709 0.3877
3.250 1.4009 0.01563 0.00799 -0.2231 0.3657 0.3932
3.500 1.4212 0.01600 0.00834 -0.2219 0.3605 0.3990
3.750 1.4433 0.01630 0.00864 -0.2210 0.3560 0.4050
4.000 1.4648 0.01664 0.00898 -0.2200 0.3505 0.4108
4.250 1.4846 0.01706 0.00940 -0.2188 0.3443 0.4181
4.500 1.5038 0.01751 0.00983 -0.2175 0.3383 0.4257
5.000 1.5422 0.01843 0.01076 -0.2151 0.3254 0.4399
5.250 1.5607 0.01895 0.01127 -0.2138 0.3201 0.4477
5.750 1.5951 0.02014 0.01245 -0.2109 0.3058 0.4625
6.000 1.6122 0.02076 0.01308 -0.2095 0.2979 0.4707
6.250 1.6260 0.02159 0.01387 -0.2077 0.2885 0.4781
6.500 1.6415 0.02233 0.01462 -0.2062 0.2803 0.4862
6.750 1.6535 0.02332 0.01558 -0.2043 0.2703 0.4942
7.000 1.6659 0.02430 0.01652 -0.2026 0.2586 0.5009
7.250 1.6750 0.02555 0.01773 -0.2005 0.2451 0.5068
7.500 1.6810 0.02704 0.01915 -0.1981 0.2284 0.5126
7.750 1.6840 0.02881 0.02081 -0.1956 0.2102 0.5179
8.000 1.6873 0.03061 0.02254 -0.1932 0.1953 0.5223
8.250 1.6937 0.03223 0.02414 -0.1912 0.1865 0.5269
8.500 1.7006 0.03383 0.02574 -0.1894 0.1803 0.5320
8.750 1.7100 0.03527 0.02720 -0.1878 0.1769 0.5374
9.000 1.7197 0.03673 0.02867 -0.1864 0.1741 0.5422
9.250 1.7280 0.03834 0.03032 -0.1849 0.1714 0.5461
9.500 1.7363 0.03997 0.03198 -0.1834 0.1690 0.5499
9.750 1.7434 0.04175 0.03380 -0.1820 0.1667 0.5538
10.000 1.7533 0.04331 0.03540 -0.1808 0.1654 0.5579
10.250 1.7623 0.04498 0.03712 -0.1796 0.1644 0.5618
10.500 1.7715 0.04663 0.03884 -0.1784 0.1633 0.5653
10.750 1.7794 0.04846 0.04073 -0.1773 0.1623 0.5688
11.000 1.7873 0.05028 0.04262 -0.1761 0.1614 0.5725
11.250 1.7941 0.05225 0.04464 -0.1750 0.1606 0.5762
11.500 1.8007 0.05427 0.04671 -0.1739 0.1598 0.5797
11.750 1.8064 0.05642 0.04891 -0.1728 0.1590 0.5827
12.000 1.8117 0.05862 0.05119 -0.1718 0.1582 0.5857
12.250 1.8162 0.06092 0.05356 -0.1708 0.1575 0.5888
12.500 1.8202 0.06330 0.05601 -0.1698 0.1568 0.5919
12.750 1.8237 0.06576 0.05853 -0.1689 0.1561 0.5949
13.000 1.8266 0.06832 0.06115 -0.1680 0.1554 0.5979
13.250 1.8294 0.07091 0.06380 -0.1671 0.1547 0.6005
13.500 1.8316 0.07359 0.06656 -0.1663 0.1541 0.6030
13.750 1.8338 0.07624 0.06928 -0.1655 0.1535 0.6055
14.000 1.8352 0.07904 0.07214 -0.1647 0.1528 0.6080
14.250 1.8379 0.08164 0.07482 -0.1641 0.1523 0.6109
14.500 1.8417 0.08418 0.07744 -0.1635 0.1520 0.6138
14.750 1.8466 0.08658 0.07991 -0.1630 0.1518 0.6168
15.000 1.8510 0.08903 0.08243 -0.1625 0.1515 0.6196
15.250 1.8547 0.09156 0.08506 -0.1620 0.1513 0.6223
15.500 1.8596 0.09394 0.08752 -0.1616 0.1510 0.6253
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