GOE 423 AIRFOIL (goe423-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 423 AIRFOIL (goe423-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.53 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe423-il-1000000-n5.txt Download as CSV file: xf-goe423-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.0959 0.04449 0.04125 -0.1159 1.0000 0.0319
-17.750 -1.1063 0.03930 0.03593 -0.1205 0.9971 0.0321
-17.500 -1.1020 0.03563 0.03213 -0.1247 0.9901 0.0324
-17.250 -1.0941 0.03286 0.02925 -0.1277 0.9833 0.0326
-17.000 -1.0865 0.03068 0.02695 -0.1293 0.9762 0.0329
-16.500 -1.0708 0.02755 0.02360 -0.1296 0.9604 0.0334
-16.250 -1.0624 0.02636 0.02231 -0.1288 0.9528 0.0337
-16.000 -1.0527 0.02534 0.02119 -0.1278 0.9449 0.0339
-15.750 -1.0415 0.02448 0.02022 -0.1265 0.9374 0.0341
-15.500 -1.0294 0.02366 0.01930 -0.1252 0.9291 0.0343
-15.250 -1.0190 0.02279 0.01835 -0.1236 0.9217 0.0346
-15.000 -1.0045 0.02215 0.01766 -0.1223 0.9135 0.0350
-14.750 -0.9891 0.02168 0.01712 -0.1208 0.9048 0.0353
-14.500 -0.9702 0.02123 0.01662 -0.1198 0.8951 0.0356
-14.250 -0.9507 0.02078 0.01609 -0.1190 0.8855 0.0359
-14.000 -0.9311 0.02032 0.01553 -0.1180 0.8738 0.0361
-13.750 -0.9110 0.01984 0.01496 -0.1172 0.8616 0.0364
-13.500 -0.8900 0.01943 0.01445 -0.1164 0.8496 0.0367
-13.000 -0.8468 0.01858 0.01340 -0.1151 0.8279 0.0373
-12.750 -0.8251 0.01815 0.01286 -0.1144 0.8163 0.0376
-12.500 -0.8027 0.01773 0.01234 -0.1137 0.8047 0.0378
-12.250 -0.7799 0.01733 0.01184 -0.1132 0.7946 0.0380
-12.000 -0.7570 0.01697 0.01137 -0.1126 0.7823 0.0382
-11.750 -0.7334 0.01663 0.01093 -0.1120 0.7674 0.0384
-11.500 -0.7099 0.01637 0.01053 -0.1115 0.7472 0.0386
-11.250 -0.6889 0.01596 0.00997 -0.1105 0.7140 0.0390
-11.000 -0.6675 0.01573 0.00954 -0.1096 0.6716 0.0393
-10.750 -0.6446 0.01550 0.00918 -0.1089 0.6464 0.0396
-10.500 -0.6206 0.01525 0.00884 -0.1084 0.6321 0.0399
-10.000 -0.5710 0.01477 0.00822 -0.1076 0.6136 0.0405
-9.750 -0.5459 0.01454 0.00792 -0.1072 0.6065 0.0408
-9.500 -0.5206 0.01431 0.00763 -0.1068 0.6006 0.0411
-9.250 -0.4949 0.01406 0.00734 -0.1065 0.5960 0.0414
-9.000 -0.4691 0.01384 0.00707 -0.1062 0.5911 0.0418
-8.750 -0.4433 0.01364 0.00681 -0.1059 0.5863 0.0422
-8.500 -0.4175 0.01344 0.00656 -0.1056 0.5819 0.0426
-8.250 -0.3913 0.01322 0.00629 -0.1054 0.5784 0.0429
-8.000 -0.3650 0.01301 0.00604 -0.1052 0.5746 0.0431
-7.750 -0.3388 0.01283 0.00581 -0.1049 0.5706 0.0434
-7.500 -0.3126 0.01264 0.00557 -0.1046 0.5668 0.0436
-7.000 -0.2609 0.01215 0.00503 -0.1040 0.5611 0.0446
-6.750 -0.2343 0.01196 0.00483 -0.1038 0.5586 0.0450
-6.500 -0.2075 0.01180 0.00464 -0.1036 0.5559 0.0455
-6.250 -0.1808 0.01165 0.00447 -0.1035 0.5531 0.0460
-6.000 -0.1539 0.01152 0.00431 -0.1033 0.5503 0.0465
-5.750 -0.1271 0.01140 0.00417 -0.1031 0.5475 0.0471
-5.250 -0.0732 0.01116 0.00387 -0.1028 0.5430 0.0481
-5.000 -0.0459 0.01103 0.00373 -0.1027 0.5412 0.0485
-4.750 -0.0186 0.01092 0.00360 -0.1026 0.5392 0.0489
-4.500 0.0083 0.01078 0.00345 -0.1024 0.5370 0.0495
-4.250 0.0351 0.01064 0.00330 -0.1022 0.5347 0.0503
-4.000 0.0621 0.01053 0.00318 -0.1021 0.5323 0.0511
-3.750 0.0891 0.01045 0.00308 -0.1019 0.5299 0.0519
-3.500 0.1160 0.01037 0.00299 -0.1017 0.5275 0.0527
-3.250 0.1432 0.01030 0.00291 -0.1016 0.5256 0.0536
-3.000 0.1708 0.01023 0.00284 -0.1016 0.5244 0.0545
-2.750 0.1985 0.01016 0.00276 -0.1015 0.5230 0.0552
-2.500 0.2258 0.01006 0.00268 -0.1014 0.5214 0.0565
-2.250 0.2532 0.00998 0.00261 -0.1014 0.5198 0.0579
-2.000 0.2806 0.00992 0.00255 -0.1013 0.5182 0.0594
-1.750 0.3080 0.00987 0.00251 -0.1012 0.5165 0.0609
-1.500 0.3354 0.00983 0.00246 -0.1012 0.5149 0.0625
-1.250 0.3625 0.00977 0.00242 -0.1010 0.5132 0.0655
-1.000 0.3896 0.00973 0.00240 -0.1009 0.5116 0.0692
-0.750 0.4165 0.00969 0.00238 -0.1008 0.5098 0.0754
-0.500 0.4432 0.00965 0.00237 -0.1006 0.5080 0.0860
-0.250 0.4703 0.00954 0.00236 -0.1006 0.5070 0.1104
0.000 0.4976 0.00946 0.00237 -0.1005 0.5058 0.1297
0.250 0.5252 0.00943 0.00238 -0.1005 0.5045 0.1414
0.500 0.5527 0.00940 0.00239 -0.1005 0.5033 0.1528
0.750 0.5800 0.00936 0.00240 -0.1005 0.5020 0.1661
1.000 0.6070 0.00929 0.00242 -0.1004 0.5006 0.1900
1.250 0.6332 0.00915 0.00246 -0.1002 0.4993 0.2533
1.500 0.6597 0.00907 0.00250 -0.1001 0.4980 0.2983
1.750 0.6848 0.00883 0.00254 -0.0998 0.4967 0.3943
2.000 0.7082 0.00848 0.00263 -0.0992 0.4953 0.5517
2.250 0.7329 0.00833 0.00270 -0.0987 0.4937 0.6303
2.500 0.7551 0.00808 0.00280 -0.0976 0.4917 0.7458
2.750 0.7766 0.00785 0.00293 -0.0962 0.4897 0.8628
3.000 0.8043 0.00780 0.00306 -0.0960 0.4875 0.9257
3.250 0.8402 0.00789 0.00318 -0.0978 0.4843 0.9542
3.500 0.8753 0.00800 0.00328 -0.0995 0.4804 0.9690
3.750 0.9083 0.00816 0.00339 -0.1008 0.4747 0.9791
4.000 0.9450 0.00825 0.00348 -0.1028 0.4683 0.9849
4.250 0.9806 0.00839 0.00358 -0.1047 0.4616 0.9902
4.500 1.0138 0.00853 0.00369 -0.1061 0.4558 0.9935
4.750 1.0531 0.00866 0.00380 -0.1089 0.4478 0.9963
5.000 1.0946 0.00885 0.00395 -0.1122 0.4397 0.9995
5.250 1.1183 0.00898 0.00405 -0.1115 0.4307 1.0000
5.500 1.1338 0.00915 0.00417 -0.1091 0.4179 1.0000
5.750 1.1425 0.00950 0.00438 -0.1055 0.3905 1.0000
6.000 1.1389 0.01004 0.00472 -0.0993 0.3533 1.0000
6.250 1.1353 0.01076 0.00522 -0.0934 0.3151 1.0000
6.500 1.1394 0.01148 0.00576 -0.0892 0.2826 1.0000
6.750 1.1461 0.01221 0.00633 -0.0857 0.2523 1.0000
7.000 1.1536 0.01299 0.00695 -0.0825 0.2230 1.0000
7.250 1.1557 0.01405 0.00781 -0.0786 0.1865 1.0000
7.500 1.1374 0.01616 0.00954 -0.0721 0.1144 1.0000
7.750 1.1384 0.01750 0.01075 -0.0686 0.0839 1.0000
8.000 1.1347 0.01923 0.01231 -0.0649 0.0459 1.0000
8.250 1.1469 0.02013 0.01320 -0.0633 0.0400 1.0000
8.500 1.1604 0.02101 0.01407 -0.0619 0.0372 1.0000
8.750 1.1739 0.02191 0.01498 -0.0607 0.0354 1.0000
9.000 1.1880 0.02280 0.01589 -0.0595 0.0342 1.0000
9.250 1.2009 0.02379 0.01690 -0.0583 0.0332 1.0000
9.500 1.2131 0.02487 0.01799 -0.0571 0.0323 1.0000
9.750 1.2245 0.02604 0.01918 -0.0559 0.0314 1.0000
10.000 1.2364 0.02721 0.02038 -0.0549 0.0308 1.0000
10.250 1.2480 0.02842 0.02162 -0.0539 0.0304 1.0000
10.500 1.2593 0.02971 0.02294 -0.0529 0.0300 1.0000
10.750 1.2697 0.03110 0.02437 -0.0520 0.0296 1.0000
11.000 1.2795 0.03260 0.02590 -0.0511 0.0292 1.0000
11.250 1.2887 0.03418 0.02751 -0.0502 0.0288 1.0000
11.500 1.2973 0.03584 0.02921 -0.0494 0.0284 1.0000
11.750 1.3054 0.03759 0.03100 -0.0486 0.0281 1.0000
12.000 1.3129 0.03944 0.03288 -0.0479 0.0277 1.0000
12.250 1.3194 0.04142 0.03490 -0.0472 0.0274 1.0000
12.500 1.3247 0.04351 0.03704 -0.0464 0.0271 1.0000
12.750 1.3312 0.04550 0.03907 -0.0458 0.0268 1.0000
13.000 1.3386 0.04741 0.04103 -0.0452 0.0267 1.0000
13.250 1.3456 0.04938 0.04305 -0.0447 0.0264 1.0000
13.500 1.3524 0.05136 0.04507 -0.0441 0.0262 1.0000
13.750 1.3582 0.05346 0.04722 -0.0436 0.0260 1.0000
14.000 1.3640 0.05555 0.04935 -0.0431 0.0258 1.0000
14.250 1.3692 0.05771 0.05156 -0.0426 0.0256 1.0000
14.500 1.3743 0.05993 0.05382 -0.0421 0.0253 1.0000
14.750 1.3797 0.06209 0.05603 -0.0417 0.0251 1.0000
15.000 1.3838 0.06445 0.05843 -0.0413 0.0249 1.0000
15.250 1.3888 0.06666 0.06069 -0.0409 0.0247 1.0000
15.500 1.3925 0.06908 0.06316 -0.0406 0.0245 1.0000
15.750 1.3966 0.07147 0.06559 -0.0403 0.0243 1.0000
16.000 1.4008 0.07384 0.06800 -0.0401 0.0240 1.0000
16.250 1.4027 0.07653 0.07074 -0.0399 0.0238 1.0000
16.500 1.4052 0.07911 0.07337 -0.0396 0.0236 1.0000
16.750 1.4052 0.08204 0.07635 -0.0395 0.0233 1.0000
17.000 1.4051 0.08500 0.07937 -0.0394 0.0231 1.0000
17.250 1.4094 0.08744 0.08186 -0.0393 0.0230 1.0000
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