GOE 675 AIRFOIL (goe675-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 675 AIRFOIL (goe675-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.89 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe675-il-1000000-n5.txt Download as CSV file: xf-goe675-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 675 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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.6257 0.08330 0.08041 -0.0898 0.9084 0.0247
-15.250 -0.6502 0.07610 0.07310 -0.0946 0.9023 0.0248
-15.000 -0.8899 0.03231 0.02859 -0.1368 0.8815 0.0245
-14.750 -0.8862 0.02876 0.02482 -0.1396 0.8759 0.0245
-14.500 -0.8738 0.02683 0.02273 -0.1405 0.8711 0.0246
-14.250 -0.8578 0.02538 0.02113 -0.1408 0.8670 0.0247
-14.000 -0.8392 0.02414 0.01980 -0.1410 0.8638 0.0248
-13.750 -0.8191 0.02309 0.01864 -0.1411 0.8602 0.0249
-13.500 -0.7979 0.02216 0.01761 -0.1411 0.8564 0.0250
-13.250 -0.7775 0.02113 0.01648 -0.1411 0.8528 0.0252
-13.000 -0.7564 0.02016 0.01540 -0.1410 0.8492 0.0254
-12.750 -0.7336 0.01933 0.01450 -0.1410 0.8462 0.0257
-12.500 -0.7098 0.01860 0.01370 -0.1409 0.8430 0.0259
-12.250 -0.6854 0.01794 0.01297 -0.1408 0.8396 0.0260
-12.000 -0.6606 0.01734 0.01230 -0.1408 0.8362 0.0262
-11.750 -0.6353 0.01680 0.01168 -0.1407 0.8328 0.0264
-11.500 -0.6098 0.01629 0.01109 -0.1406 0.8296 0.0266
-11.250 -0.5835 0.01580 0.01055 -0.1406 0.8268 0.0268
-11.000 -0.5571 0.01533 0.01003 -0.1405 0.8236 0.0270
-10.750 -0.5305 0.01490 0.00953 -0.1405 0.8204 0.0273
-10.500 -0.5037 0.01449 0.00906 -0.1405 0.8170 0.0275
-10.250 -0.4768 0.01411 0.00861 -0.1404 0.8137 0.0277
-10.000 -0.4496 0.01376 0.00819 -0.1404 0.8106 0.0280
-9.750 -0.4220 0.01341 0.00779 -0.1404 0.8078 0.0282
-9.500 -0.3943 0.01308 0.00742 -0.1405 0.8047 0.0284
-9.250 -0.3665 0.01278 0.00707 -0.1405 0.8012 0.0286
-9.000 -0.3391 0.01240 0.00663 -0.1405 0.7977 0.0290
-8.750 -0.3116 0.01207 0.00625 -0.1404 0.7941 0.0294
-8.500 -0.2835 0.01176 0.00591 -0.1405 0.7908 0.0298
-8.250 -0.2554 0.01147 0.00559 -0.1406 0.7863 0.0302
-8.000 -0.2273 0.01123 0.00530 -0.1406 0.7809 0.0308
-7.750 -0.1993 0.01101 0.00502 -0.1405 0.7758 0.0313
-7.500 -0.1707 0.01079 0.00477 -0.1406 0.7716 0.0319
-7.250 -0.1420 0.01058 0.00453 -0.1407 0.7673 0.0323
-7.000 -0.1137 0.01035 0.00427 -0.1407 0.7624 0.0331
-6.750 -0.0855 0.01015 0.00402 -0.1407 0.7574 0.0341
-6.500 -0.0568 0.00994 0.00381 -0.1408 0.7526 0.0352
-6.250 -0.0281 0.00977 0.00361 -0.1409 0.7473 0.0364
-6.000 0.0002 0.00958 0.00339 -0.1409 0.7417 0.0388
-5.750 0.0287 0.00938 0.00320 -0.1410 0.7366 0.0427
-5.500 0.0573 0.00919 0.00305 -0.1411 0.7307 0.0501
-5.250 0.0859 0.00909 0.00295 -0.1411 0.7244 0.0567
-5.000 0.1147 0.00902 0.00287 -0.1412 0.7179 0.0609
-4.750 0.1434 0.00896 0.00279 -0.1412 0.7095 0.0635
-4.500 0.1720 0.00892 0.00272 -0.1412 0.7022 0.0661
-4.250 0.2009 0.00887 0.00265 -0.1413 0.6955 0.0680
-4.000 0.2295 0.00883 0.00257 -0.1414 0.6887 0.0694
-3.750 0.2582 0.00877 0.00250 -0.1414 0.6817 0.0710
-3.500 0.2867 0.00874 0.00245 -0.1414 0.6732 0.0728
-3.250 0.3151 0.00872 0.00239 -0.1414 0.6652 0.0743
-3.000 0.3436 0.00871 0.00234 -0.1414 0.6567 0.0755
-2.750 0.3719 0.00871 0.00230 -0.1414 0.6486 0.0763
-2.500 0.4000 0.00866 0.00223 -0.1414 0.6386 0.0781
-2.250 0.4278 0.00866 0.00220 -0.1413 0.6280 0.0800
-2.000 0.4553 0.00868 0.00217 -0.1411 0.6162 0.0813
-1.750 0.4834 0.00869 0.00215 -0.1411 0.6052 0.0825
-1.500 0.5107 0.00873 0.00214 -0.1409 0.5929 0.0838
-1.250 0.5377 0.00881 0.00215 -0.1407 0.5777 0.0850
-1.000 0.5641 0.00888 0.00215 -0.1403 0.5597 0.0870
-0.750 0.5902 0.00898 0.00218 -0.1399 0.5397 0.0887
-0.500 0.6159 0.00911 0.00223 -0.1395 0.5181 0.0905
-0.250 0.6409 0.00928 0.00230 -0.1389 0.4944 0.0924
0.000 0.6656 0.00947 0.00239 -0.1383 0.4724 0.0944
0.250 0.6908 0.00963 0.00247 -0.1378 0.4547 0.0983
0.500 0.7168 0.00973 0.00255 -0.1374 0.4419 0.1034
0.750 0.7430 0.00982 0.00263 -0.1371 0.4327 0.1105
1.000 0.7693 0.00990 0.00271 -0.1367 0.4241 0.1203
1.250 0.7953 0.01000 0.00280 -0.1364 0.4164 0.1320
1.500 0.8218 0.01006 0.00288 -0.1361 0.4099 0.1447
1.750 0.8478 0.01014 0.00298 -0.1358 0.4037 0.1578
2.000 0.8738 0.01022 0.00307 -0.1355 0.3986 0.1744
2.250 0.9004 0.01023 0.00317 -0.1353 0.3943 0.2068
2.500 0.9264 0.01026 0.00330 -0.1350 0.3892 0.2526
2.750 0.9517 0.01034 0.00344 -0.1346 0.3839 0.2849
3.000 0.9774 0.01042 0.00356 -0.1342 0.3799 0.3115
3.250 1.0035 0.01045 0.00369 -0.1339 0.3765 0.3439
3.500 1.0292 0.01043 0.00384 -0.1336 0.3722 0.4193
3.750 1.0536 0.01032 0.00406 -0.1333 0.3663 0.5786
4.250 1.1002 0.00984 0.00447 -0.1315 0.3565 1.0000
4.500 1.1234 0.01004 0.00463 -0.1306 0.3500 1.0000
4.750 1.1449 0.01027 0.00481 -0.1294 0.3432 1.0000
5.000 1.1676 0.01045 0.00497 -0.1285 0.3373 1.0000
5.250 1.1893 0.01069 0.00518 -0.1274 0.3312 1.0000
5.500 1.2112 0.01093 0.00539 -0.1264 0.3256 1.0000
5.750 1.2340 0.01115 0.00559 -0.1256 0.3203 1.0000
6.000 1.2552 0.01143 0.00584 -0.1245 0.3137 1.0000
6.250 1.2769 0.01171 0.00609 -0.1235 0.3080 1.0000
6.500 1.2986 0.01199 0.00635 -0.1226 0.3010 1.0000
6.750 1.3184 0.01236 0.00668 -0.1214 0.2935 1.0000
7.000 1.3397 0.01267 0.00697 -0.1204 0.2859 1.0000
7.250 1.3587 0.01310 0.00735 -0.1191 0.2775 1.0000
7.500 1.3785 0.01349 0.00772 -0.1180 0.2682 1.0000
7.750 1.3971 0.01396 0.00814 -0.1167 0.2592 1.0000
8.000 1.4146 0.01449 0.00862 -0.1153 0.2483 1.0000
8.250 1.4315 0.01507 0.00913 -0.1139 0.2356 1.0000
8.500 1.4467 0.01574 0.00973 -0.1122 0.2216 1.0000
8.750 1.4605 0.01651 0.01042 -0.1104 0.2057 1.0000
9.000 1.4720 0.01743 0.01123 -0.1083 0.1883 1.0000
9.250 1.4837 0.01836 0.01206 -0.1064 0.1718 1.0000
9.500 1.4952 0.01931 0.01294 -0.1044 0.1573 1.0000
9.750 1.5047 0.02042 0.01394 -0.1023 0.1397 1.0000
10.000 1.5116 0.02169 0.01510 -0.1000 0.1213 1.0000
10.250 1.5139 0.02331 0.01657 -0.0972 0.0964 1.0000
10.500 1.5172 0.02491 0.01805 -0.0946 0.0780 1.0000
10.750 1.5225 0.02640 0.01949 -0.0924 0.0644 1.0000
11.000 1.5177 0.02868 0.02162 -0.0893 0.0387 1.0000
11.250 1.5266 0.03001 0.02295 -0.0876 0.0345 1.0000
11.500 1.5371 0.03125 0.02421 -0.0862 0.0326 1.0000
11.750 1.5475 0.03254 0.02552 -0.0849 0.0312 1.0000
12.000 1.5587 0.03379 0.02680 -0.0837 0.0304 1.0000
12.250 1.5693 0.03511 0.02816 -0.0826 0.0297 1.0000
12.500 1.5788 0.03655 0.02963 -0.0814 0.0290 1.0000
12.750 1.5877 0.03807 0.03119 -0.0802 0.0284 1.0000
13.000 1.5960 0.03968 0.03284 -0.0790 0.0279 1.0000
13.250 1.6032 0.04143 0.03463 -0.0779 0.0274 1.0000
13.500 1.6113 0.04313 0.03638 -0.0769 0.0271 1.0000
13.750 1.6189 0.04491 0.03822 -0.0760 0.0268 1.0000
14.000 1.6262 0.04673 0.04009 -0.0750 0.0266 1.0000
14.250 1.6324 0.04872 0.04213 -0.0742 0.0263 1.0000
14.500 1.6380 0.05080 0.04427 -0.0733 0.0261 1.0000
14.750 1.6431 0.05296 0.04649 -0.0726 0.0258 1.0000
15.000 1.6466 0.05535 0.04894 -0.0719 0.0255 1.0000
15.250 1.6494 0.05783 0.05148 -0.0712 0.0252 1.0000
15.500 1.6515 0.06041 0.05412 -0.0706 0.0249 1.0000
15.750 1.6520 0.06326 0.05704 -0.0700 0.0247 1.0000
16.000 1.6516 0.06626 0.06011 -0.0696 0.0244 1.0000
16.250 1.6502 0.06942 0.06335 -0.0692 0.0242 1.0000
16.500 1.6475 0.07276 0.06676 -0.0689 0.0240 1.0000
16.750 1.6431 0.07638 0.07047 -0.0687 0.0238 1.0000
17.000 1.6371 0.08028 0.07445 -0.0687 0.0235 1.0000
17.250 1.6329 0.08401 0.07826 -0.0688 0.0234 1.0000
17.500 1.6297 0.08764 0.08198 -0.0690 0.0233 1.0000
17.750 1.6256 0.09140 0.08582 -0.0692 0.0231 1.0000
18.000 1.6209 0.09526 0.08978 -0.0696 0.0230 1.0000
18.250 1.6160 0.09921 0.09381 -0.0701 0.0228 1.0000
18.500 1.6107 0.10323 0.09792 -0.0707 0.0227 1.0000
18.750 1.6046 0.10742 0.10219 -0.0714 0.0226 1.0000
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