GOE 480 AIRFOIL (goe480-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 480 AIRFOIL (goe480-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.76 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe480-il-1000000-n5.txt Download as CSV file: xf-goe480-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 480 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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.4278 0.16864 0.16673 -0.0258 1.0000 0.0112
-16.750 -0.4200 0.16609 0.16418 -0.0270 1.0000 0.0114
-14.750 -0.9786 0.03067 0.02823 -0.1185 0.9881 0.0285
-14.500 -0.9620 0.02746 0.02478 -0.1217 0.9840 0.0291
-14.250 -0.9326 0.02754 0.02491 -0.1218 0.9806 0.0296
-14.000 -0.8995 0.02808 0.02552 -0.1220 0.9773 0.0302
-13.750 -0.8685 0.02756 0.02497 -0.1233 0.9742 0.0308
-13.500 -0.8421 0.02607 0.02334 -0.1253 0.9695 0.0315
-13.250 -0.8153 0.02432 0.02140 -0.1275 0.9641 0.0322
-13.000 -0.7885 0.02260 0.01947 -0.1296 0.9576 0.0328
-12.750 -0.7600 0.02124 0.01790 -0.1313 0.9492 0.0332
-12.500 -0.7306 0.02059 0.01716 -0.1324 0.9381 0.0336
-12.250 -0.6999 0.02048 0.01703 -0.1330 0.9257 0.0340
-12.000 -0.6715 0.02039 0.01689 -0.1331 0.9114 0.0343
-11.750 -0.6443 0.02041 0.01685 -0.1329 0.8961 0.0345
-11.500 -0.6175 0.02054 0.01694 -0.1325 0.8799 0.0348
-11.250 -0.5923 0.02055 0.01688 -0.1319 0.8635 0.0351
-11.000 -0.5693 0.02027 0.01649 -0.1311 0.8480 0.0354
-10.750 -0.5449 0.02020 0.01633 -0.1305 0.8334 0.0358
-10.500 -0.5227 0.01973 0.01573 -0.1298 0.8194 0.0362
-10.250 -0.5008 0.01916 0.01501 -0.1290 0.8074 0.0367
-10.000 -0.4791 0.01852 0.01420 -0.1283 0.7959 0.0372
-9.750 -0.4572 0.01783 0.01334 -0.1276 0.7852 0.0376
-9.500 -0.4338 0.01733 0.01270 -0.1269 0.7760 0.0379
-9.250 -0.4104 0.01680 0.01203 -0.1263 0.7672 0.0381
-9.000 -0.3865 0.01629 0.01139 -0.1258 0.7599 0.0383
-8.750 -0.3639 0.01549 0.01043 -0.1251 0.7527 0.0386
-8.250 -0.3144 0.01462 0.00940 -0.1241 0.7403 0.0392
-8.000 -0.2888 0.01430 0.00901 -0.1237 0.7342 0.0395
-7.750 -0.2634 0.01400 0.00862 -0.1232 0.7283 0.0397
-7.500 -0.2371 0.01369 0.00827 -0.1229 0.7236 0.0399
-7.250 -0.2110 0.01340 0.00791 -0.1225 0.7181 0.0401
-7.000 -0.1850 0.01311 0.00755 -0.1221 0.7128 0.0404
-6.750 -0.1587 0.01282 0.00719 -0.1218 0.7083 0.0406
-6.500 -0.1320 0.01258 0.00690 -0.1215 0.7033 0.0410
-6.250 -0.1055 0.01232 0.00658 -0.1211 0.6983 0.0413
-5.750 -0.0526 0.01170 0.00583 -0.1204 0.6888 0.0419
-5.500 -0.0259 0.01142 0.00549 -0.1201 0.6838 0.0422
-5.250 0.0006 0.01115 0.00516 -0.1197 0.6786 0.0425
-5.000 0.0274 0.01090 0.00484 -0.1194 0.6740 0.0428
-4.750 0.0544 0.01066 0.00456 -0.1191 0.6689 0.0431
-4.500 0.0813 0.01044 0.00429 -0.1188 0.6632 0.0434
-4.250 0.1080 0.01026 0.00405 -0.1184 0.6580 0.0436
-4.000 0.1354 0.01008 0.00384 -0.1182 0.6526 0.0438
-3.750 0.1624 0.00992 0.00364 -0.1179 0.6462 0.0440
-3.500 0.1893 0.00979 0.00346 -0.1176 0.6404 0.0442
-3.250 0.2166 0.00964 0.00329 -0.1173 0.6340 0.0443
-3.000 0.2426 0.00933 0.00293 -0.1169 0.6268 0.0451
-2.750 0.2695 0.00918 0.00276 -0.1165 0.6203 0.0456
-2.500 0.2964 0.00906 0.00262 -0.1162 0.6121 0.0460
-2.250 0.3232 0.00897 0.00249 -0.1158 0.6044 0.0463
-2.000 0.3502 0.00889 0.00239 -0.1155 0.5957 0.0467
-1.750 0.3769 0.00882 0.00229 -0.1152 0.5873 0.0471
-1.500 0.4038 0.00877 0.00220 -0.1148 0.5782 0.0476
-1.250 0.4305 0.00872 0.00212 -0.1144 0.5697 0.0480
-1.000 0.4570 0.00869 0.00205 -0.1140 0.5598 0.0485
-0.750 0.4838 0.00865 0.00198 -0.1137 0.5511 0.0490
-0.500 0.5101 0.00865 0.00194 -0.1133 0.5415 0.0496
-0.250 0.5369 0.00863 0.00189 -0.1129 0.5330 0.0501
0.000 0.5632 0.00865 0.00187 -0.1125 0.5238 0.0506
0.250 0.5900 0.00865 0.00185 -0.1121 0.5154 0.0510
0.500 0.6161 0.00870 0.00186 -0.1117 0.5057 0.0514
0.750 0.6425 0.00868 0.00183 -0.1113 0.4959 0.0523
1.000 0.6685 0.00870 0.00181 -0.1108 0.4866 0.0533
1.250 0.6947 0.00873 0.00181 -0.1104 0.4771 0.0544
1.500 0.7209 0.00876 0.00184 -0.1100 0.4692 0.0553
1.750 0.7472 0.00880 0.00186 -0.1096 0.4613 0.0564
2.000 0.7731 0.00886 0.00190 -0.1091 0.4534 0.0576
2.250 0.7994 0.00891 0.00194 -0.1087 0.4454 0.0587
2.500 0.8250 0.00899 0.00200 -0.1082 0.4373 0.0599
2.750 0.8513 0.00904 0.00206 -0.1078 0.4303 0.0624
3.250 0.9022 0.00915 0.00221 -0.1068 0.4144 0.0886
3.500 0.9264 0.00914 0.00235 -0.1061 0.4057 0.1749
3.750 0.9517 0.00917 0.00245 -0.1056 0.3987 0.2100
4.000 0.9747 0.00901 0.00263 -0.1048 0.3910 0.3768
4.250 0.9943 0.00860 0.00284 -0.1033 0.3847 0.6526
4.750 1.0783 0.00844 0.00328 -0.1098 0.3598 1.0000
5.000 1.1009 0.00865 0.00343 -0.1088 0.3478 1.0000
5.250 1.1232 0.00888 0.00360 -0.1077 0.3369 1.0000
5.500 1.1464 0.00905 0.00375 -0.1068 0.3286 1.0000
5.750 1.1687 0.00927 0.00392 -0.1057 0.3198 1.0000
6.000 1.1909 0.00949 0.00410 -0.1046 0.3099 1.0000
6.250 1.2126 0.00972 0.00430 -0.1035 0.2996 1.0000
6.500 1.2334 0.01000 0.00452 -0.1022 0.2889 1.0000
6.750 1.2549 0.01023 0.00472 -0.1010 0.2796 1.0000
7.000 1.2755 0.01049 0.00495 -0.0997 0.2707 1.0000
7.500 1.3134 0.01113 0.00548 -0.0965 0.2464 1.0000
7.750 1.3288 0.01150 0.00579 -0.0942 0.2320 1.0000
8.000 1.3437 0.01186 0.00609 -0.0918 0.2197 1.0000
8.250 1.3578 0.01227 0.00644 -0.0894 0.2067 1.0000
8.500 1.3719 0.01271 0.00681 -0.0870 0.1938 1.0000
8.750 1.3849 0.01321 0.00724 -0.0846 0.1785 1.0000
9.000 1.3973 0.01376 0.00771 -0.0821 0.1627 1.0000
9.250 1.4066 0.01447 0.00831 -0.0792 0.1421 1.0000
9.500 1.4114 0.01543 0.00912 -0.0758 0.1158 1.0000
9.750 1.4126 0.01664 0.01016 -0.0721 0.0882 1.0000
10.000 1.4204 0.01758 0.01103 -0.0695 0.0749 1.0000
10.250 1.4307 0.01843 0.01185 -0.0674 0.0663 1.0000
10.500 1.4436 0.01917 0.01260 -0.0657 0.0617 1.0000
10.750 1.4545 0.02007 0.01348 -0.0639 0.0566 1.0000
11.000 1.4680 0.02084 0.01428 -0.0624 0.0536 1.0000
11.250 1.4793 0.02179 0.01523 -0.0608 0.0493 1.0000
11.500 1.4912 0.02273 0.01619 -0.0594 0.0463 1.0000
11.750 1.5025 0.02375 0.01722 -0.0580 0.0422 1.0000
12.000 1.5124 0.02492 0.01839 -0.0566 0.0384 1.0000
12.250 1.5205 0.02624 0.01971 -0.0552 0.0337 1.0000
12.500 1.5293 0.02757 0.02105 -0.0539 0.0303 1.0000
13.000 1.5459 0.03039 0.02392 -0.0515 0.0259 1.0000
13.250 1.5528 0.03197 0.02552 -0.0504 0.0241 1.0000
13.500 1.5593 0.03362 0.02721 -0.0493 0.0225 1.0000
13.750 1.5665 0.03523 0.02887 -0.0483 0.0215 1.0000
14.000 1.5717 0.03706 0.03074 -0.0473 0.0203 1.0000
14.250 1.5760 0.03902 0.03275 -0.0464 0.0192 1.0000
14.500 1.5816 0.04091 0.03469 -0.0456 0.0185 1.0000
14.750 1.5858 0.04295 0.03679 -0.0449 0.0177 1.0000
15.000 1.5888 0.04516 0.03905 -0.0442 0.0170 1.0000
15.250 1.5908 0.04753 0.04148 -0.0436 0.0163 1.0000
15.500 1.5925 0.05000 0.04400 -0.0430 0.0157 1.0000
15.750 1.5947 0.05244 0.04651 -0.0426 0.0152 1.0000
16.000 1.5958 0.05504 0.04919 -0.0422 0.0149 1.0000
16.250 1.5958 0.05783 0.05204 -0.0419 0.0143 1.0000
16.500 1.5949 0.06078 0.05505 -0.0418 0.0139 1.0000
16.750 1.5924 0.06394 0.05827 -0.0416 0.0132 1.0000
17.000 1.5896 0.06719 0.06160 -0.0416 0.0130 1.0000
17.250 1.5876 0.07042 0.06490 -0.0417 0.0127 1.0000
17.500 1.5851 0.07373 0.06830 -0.0419 0.0125 1.0000
17.750 1.5816 0.07722 0.07187 -0.0421 0.0121 1.0000
18.000 1.5774 0.08080 0.07553 -0.0424 0.0119 1.0000
18.250 1.5726 0.08452 0.07933 -0.0429 0.0117 1.0000
18.500 1.5663 0.08854 0.08343 -0.0435 0.0114 1.0000
18.750 1.5597 0.09266 0.08762 -0.0442 0.0111 1.0000
19.000 1.5525 0.09687 0.09191 -0.0451 0.0109 1.0000
19.250 1.5456 0.10114 0.09625 -0.0461 0.0107 1.0000
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Polar data table (+)
Polar graphs
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