GOE 423 AIRFOIL (goe423-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 423 AIRFOIL (goe423-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.36 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe423-il-1000000.txt Download as CSV file: xf-goe423-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 423 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.8631 0.05704 0.05446 -0.1067 1.0000 0.0367
-16.250 -0.9271 0.04641 0.04358 -0.1132 1.0000 0.0367
-16.000 -0.9299 0.04081 0.03779 -0.1204 0.9972 0.0370
-15.750 -0.9240 0.03697 0.03380 -0.1256 0.9946 0.0373
-15.500 -0.9134 0.03420 0.03088 -0.1292 0.9921 0.0377
-15.250 -0.9027 0.03218 0.02873 -0.1312 0.9870 0.0380
-15.000 -0.8882 0.03059 0.02701 -0.1327 0.9824 0.0383
-14.750 -0.8792 0.02938 0.02567 -0.1322 0.9743 0.0385
-14.500 -0.8696 0.02849 0.02467 -0.1310 0.9665 0.0387
-14.250 -0.8781 0.02621 0.02220 -0.1278 0.9561 0.0392
-14.000 -0.8690 0.02539 0.02133 -0.1257 0.9484 0.0395
-13.750 -0.8542 0.02484 0.02074 -0.1242 0.9412 0.0398
-13.500 -0.8372 0.02432 0.02018 -0.1230 0.9347 0.0401
-13.250 -0.8196 0.02379 0.01959 -0.1219 0.9274 0.0404
-13.000 -0.8010 0.02334 0.01906 -0.1208 0.9207 0.0407
-12.750 -0.7815 0.02285 0.01851 -0.1199 0.9125 0.0411
-12.500 -0.7622 0.02231 0.01787 -0.1189 0.9050 0.0415
-12.250 -0.7421 0.02169 0.01717 -0.1181 0.8966 0.0418
-12.000 -0.7222 0.02107 0.01643 -0.1172 0.8879 0.0422
-11.750 -0.7011 0.02047 0.01572 -0.1165 0.8785 0.0426
-11.500 -0.6793 0.02001 0.01513 -0.1158 0.8693 0.0430
-11.250 -0.6565 0.01962 0.01464 -0.1152 0.8594 0.0433
-11.000 -0.6334 0.01928 0.01417 -0.1145 0.8498 0.0435
-10.750 -0.6143 0.01803 0.01276 -0.1137 0.8391 0.0440
-10.500 -0.5922 0.01726 0.01193 -0.1131 0.8288 0.0445
-10.250 -0.5688 0.01682 0.01141 -0.1125 0.8173 0.0449
-10.000 -0.5445 0.01645 0.01098 -0.1121 0.8048 0.0453
-9.750 -0.5201 0.01614 0.01059 -0.1116 0.7911 0.0457
-9.500 -0.4957 0.01589 0.01025 -0.1111 0.7740 0.0462
-9.250 -0.4718 0.01563 0.00986 -0.1105 0.7500 0.0466
-9.000 -0.4491 0.01539 0.00944 -0.1096 0.7135 0.0471
-8.750 -0.4269 0.01522 0.00904 -0.1087 0.6736 0.0475
-8.500 -0.4032 0.01499 0.00867 -0.1080 0.6511 0.0479
-8.250 -0.3788 0.01476 0.00832 -0.1075 0.6370 0.0483
-8.000 -0.3535 0.01454 0.00800 -0.1071 0.6272 0.0486
-7.750 -0.3280 0.01435 0.00773 -0.1067 0.6192 0.0489
-7.500 -0.3037 0.01382 0.00713 -0.1062 0.6132 0.0494
-7.250 -0.2799 0.01332 0.00659 -0.1056 0.6073 0.0503
-7.000 -0.2545 0.01308 0.00632 -0.1053 0.6018 0.0508
-6.750 -0.2282 0.01284 0.00606 -0.1050 0.5980 0.0514
-6.500 -0.2021 0.01262 0.00582 -0.1048 0.5939 0.0519
-6.250 -0.1761 0.01243 0.00558 -0.1044 0.5898 0.0525
-6.000 -0.1503 0.01226 0.00536 -0.1041 0.5854 0.0531
-5.750 -0.1237 0.01207 0.00514 -0.1039 0.5823 0.0538
-5.500 -0.0969 0.01188 0.00493 -0.1037 0.5796 0.0543
-5.250 -0.0700 0.01173 0.00475 -0.1035 0.5764 0.0548
-5.000 -0.0435 0.01157 0.00456 -0.1033 0.5732 0.0553
-4.750 -0.0191 0.01121 0.00417 -0.1027 0.5701 0.0566
-4.500 0.0068 0.01107 0.00400 -0.1024 0.5666 0.0575
-4.250 0.0337 0.01093 0.00385 -0.1022 0.5643 0.0584
-4.000 0.0608 0.01078 0.00371 -0.1021 0.5624 0.0593
-3.750 0.0880 0.01066 0.00357 -0.1020 0.5603 0.0603
-3.500 0.1153 0.01055 0.00345 -0.1018 0.5581 0.0611
-3.250 0.1426 0.01047 0.00335 -0.1017 0.5558 0.0618
-3.000 0.1686 0.01028 0.00314 -0.1014 0.5536 0.0636
-2.750 0.1952 0.01018 0.00304 -0.1012 0.5512 0.0654
-2.500 0.2221 0.01015 0.00298 -0.1010 0.5484 0.0672
-2.250 0.2495 0.01009 0.00292 -0.1009 0.5465 0.0688
-2.000 0.2769 0.00997 0.00281 -0.1009 0.5452 0.0712
-1.750 0.3042 0.00986 0.00273 -0.1008 0.5435 0.0747
-1.500 0.3317 0.00979 0.00267 -0.1007 0.5417 0.0786
-1.250 0.3587 0.00967 0.00261 -0.1006 0.5399 0.0881
-1.000 0.3852 0.00951 0.00258 -0.1004 0.5382 0.1210
-0.750 0.4121 0.00941 0.00257 -0.1003 0.5364 0.1462
-0.500 0.4392 0.00937 0.00257 -0.1002 0.5347 0.1626
-0.250 0.4661 0.00933 0.00257 -0.1001 0.5327 0.1817
0.000 0.4925 0.00924 0.00261 -0.1000 0.5305 0.2280
0.250 0.5189 0.00910 0.00266 -0.0999 0.5289 0.2897
0.500 0.5447 0.00886 0.00266 -0.0996 0.5279 0.3657
0.750 0.5678 0.00842 0.00271 -0.0989 0.5268 0.5314
1.000 0.5932 0.00825 0.00276 -0.0986 0.5255 0.6068
1.250 0.6165 0.00797 0.00281 -0.0977 0.5241 0.7075
1.500 0.6364 0.00763 0.00293 -0.0959 0.5226 0.8509
1.750 0.6638 0.00759 0.00307 -0.0955 0.5212 0.9209
2.000 0.7029 0.00772 0.00324 -0.0978 0.5198 0.9566
2.250 0.7416 0.00788 0.00338 -0.1002 0.5184 0.9731
2.500 0.7818 0.00804 0.00352 -0.1029 0.5169 0.9821
2.750 0.8243 0.00820 0.00363 -0.1062 0.5148 0.9852
3.000 0.8620 0.00836 0.00375 -0.1085 0.5113 0.9883
3.250 0.8986 0.00838 0.00379 -0.1105 0.5083 0.9925
3.500 0.9411 0.00840 0.00380 -0.1138 0.5042 0.9947
3.750 0.9807 0.00845 0.00383 -0.1166 0.5006 0.9968
4.000 1.0174 0.00858 0.00391 -0.1187 0.4957 0.9988
4.250 1.0505 0.00863 0.00396 -0.1201 0.4924 1.0000
4.500 1.0718 0.00865 0.00400 -0.1189 0.4896 1.0000
4.750 1.0929 0.00868 0.00405 -0.1176 0.4868 1.0000
5.000 1.1127 0.00874 0.00409 -0.1161 0.4827 1.0000
5.250 1.1309 0.00887 0.00418 -0.1142 0.4779 1.0000
5.500 1.1519 0.00889 0.00424 -0.1129 0.4746 1.0000
5.750 1.1723 0.00893 0.00430 -0.1115 0.4702 1.0000
6.000 1.1903 0.00902 0.00438 -0.1096 0.4647 1.0000
6.250 1.2084 0.00912 0.00447 -0.1077 0.4583 1.0000
6.500 1.2269 0.00920 0.00455 -0.1060 0.4506 1.0000
6.750 1.2419 0.00934 0.00466 -0.1035 0.4424 1.0000
7.000 1.2537 0.00948 0.00478 -0.1003 0.4304 1.0000
7.250 1.2648 0.00974 0.00496 -0.0971 0.4101 1.0000
7.500 1.2630 0.01057 0.00550 -0.0918 0.3576 1.0000
7.750 1.2566 0.01185 0.00644 -0.0860 0.3016 1.0000
8.000 1.2530 0.01313 0.00745 -0.0811 0.2534 1.0000
8.250 1.2468 0.01463 0.00866 -0.0761 0.2035 1.0000
8.500 1.2242 0.01706 0.01069 -0.0693 0.1312 1.0000
8.750 1.2085 0.01944 0.01282 -0.0640 0.0818 1.0000
9.000 1.2005 0.02161 0.01482 -0.0603 0.0480 1.0000
9.250 1.2092 0.02285 0.01606 -0.0585 0.0431 1.0000
9.500 1.2200 0.02399 0.01722 -0.0571 0.0410 1.0000
9.750 1.2292 0.02529 0.01853 -0.0557 0.0391 1.0000
10.000 1.2392 0.02658 0.01985 -0.0544 0.0379 1.0000
10.250 1.2502 0.02782 0.02113 -0.0533 0.0371 1.0000
10.500 1.2601 0.02919 0.02254 -0.0522 0.0363 1.0000
10.750 1.2690 0.03070 0.02409 -0.0511 0.0356 1.0000
11.000 1.2768 0.03235 0.02577 -0.0500 0.0349 1.0000
11.250 1.2831 0.03419 0.02765 -0.0489 0.0343 1.0000
11.500 1.2872 0.03627 0.02978 -0.0478 0.0336 1.0000
11.750 1.2929 0.03827 0.03184 -0.0470 0.0332 1.0000
12.000 1.3010 0.04007 0.03369 -0.0463 0.0329 1.0000
12.250 1.3085 0.04195 0.03562 -0.0456 0.0325 1.0000
12.500 1.3152 0.04393 0.03764 -0.0450 0.0320 1.0000
12.750 1.3210 0.04600 0.03976 -0.0443 0.0316 1.0000
13.000 1.3265 0.04811 0.04192 -0.0437 0.0313 1.0000
13.250 1.3310 0.05034 0.04420 -0.0430 0.0309 1.0000
13.500 1.3351 0.05262 0.04652 -0.0424 0.0306 1.0000
13.750 1.3385 0.05496 0.04891 -0.0418 0.0303 1.0000
14.000 1.3403 0.05752 0.05151 -0.0412 0.0299 1.0000
14.250 1.3412 0.06016 0.05420 -0.0406 0.0296 1.0000
14.500 1.3393 0.06317 0.05727 -0.0400 0.0293 1.0000
14.750 1.3348 0.06643 0.06059 -0.0394 0.0289 1.0000
15.000 1.3385 0.06887 0.06309 -0.0390 0.0287 1.0000
15.250 1.3449 0.07101 0.06527 -0.0388 0.0285 1.0000
15.500 1.3493 0.07341 0.06773 -0.0385 0.0283 1.0000
15.750 1.3533 0.07586 0.07024 -0.0383 0.0280 1.0000
16.000 1.3574 0.07828 0.07270 -0.0381 0.0278 1.0000
16.250 1.3596 0.08095 0.07543 -0.0379 0.0275 1.0000
16.500 1.3632 0.08347 0.07799 -0.0378 0.0273 1.0000
16.750 1.3663 0.08606 0.08063 -0.0377 0.0270 1.0000
17.000 1.3688 0.08876 0.08338 -0.0377 0.0267 1.0000
17.250 1.3724 0.09130 0.08596 -0.0377 0.0265 1.0000
17.500 1.3751 0.09396 0.08866 -0.0378 0.0262 1.0000
17.750 1.3771 0.09672 0.09146 -0.0378 0.0259 1.0000
18.000 1.3794 0.09941 0.09418 -0.0379 0.0256 1.0000
18.250 1.3794 0.10240 0.09721 -0.0381 0.0254 1.0000
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