GOE 476 AIRFOIL (goe476-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 476 AIRFOIL (goe476-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.51 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe476-il-1000000-n5.txt Download as CSV file: xf-goe476-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 476 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
------ -------- --------- --------- -------- -------- --------
-16.000 -1.0948 0.02856 0.02498 -0.1244 0.9895 0.0332
-15.750 -1.0852 0.02698 0.02330 -0.1241 0.9844 0.0334
-15.500 -1.0675 0.02564 0.02188 -0.1244 0.9809 0.0336
-15.250 -1.0535 0.02455 0.02071 -0.1235 0.9745 0.0338
-15.000 -1.0317 0.02355 0.01965 -0.1237 0.9702 0.0341
-14.750 -1.0061 0.02265 0.01867 -0.1245 0.9665 0.0344
-14.500 -0.9823 0.02188 0.01783 -0.1247 0.9600 0.0348
-14.250 -0.9503 0.02103 0.01690 -0.1266 0.9555 0.0351
-14.000 -0.9166 0.02022 0.01600 -0.1287 0.9504 0.0354
-13.750 -0.8846 0.01946 0.01515 -0.1303 0.9424 0.0357
-13.500 -0.8510 0.01875 0.01434 -0.1322 0.9334 0.0360
-13.250 -0.8197 0.01811 0.01358 -0.1335 0.9203 0.0363
-13.000 -0.7933 0.01760 0.01294 -0.1337 0.9032 0.0366
-12.750 -0.7709 0.01716 0.01237 -0.1329 0.8844 0.0367
-12.500 -0.7515 0.01673 0.01180 -0.1316 0.8657 0.0370
-12.250 -0.7336 0.01628 0.01123 -0.1299 0.8480 0.0374
-12.000 -0.7141 0.01590 0.01077 -0.1284 0.8334 0.0377
-11.750 -0.6934 0.01559 0.01038 -0.1271 0.8207 0.0381
-11.500 -0.6725 0.01529 0.00999 -0.1258 0.8094 0.0384
-11.250 -0.6504 0.01499 0.00963 -0.1248 0.7993 0.0388
-11.000 -0.6286 0.01471 0.00926 -0.1236 0.7894 0.0391
-10.750 -0.6060 0.01442 0.00890 -0.1226 0.7798 0.0395
-10.500 -0.5837 0.01416 0.00855 -0.1215 0.7702 0.0398
-10.250 -0.5606 0.01388 0.00820 -0.1205 0.7603 0.0402
-10.000 -0.5378 0.01364 0.00787 -0.1194 0.7499 0.0405
-9.750 -0.5144 0.01339 0.00754 -0.1185 0.7391 0.0408
-9.500 -0.4910 0.01317 0.00724 -0.1175 0.7286 0.0411
-9.250 -0.4673 0.01296 0.00695 -0.1166 0.7180 0.0413
-9.000 -0.4441 0.01267 0.00659 -0.1156 0.7087 0.0418
-8.750 -0.4206 0.01244 0.00630 -0.1146 0.6983 0.0424
-8.500 -0.3962 0.01224 0.00605 -0.1138 0.6890 0.0429
-8.250 -0.3720 0.01207 0.00582 -0.1130 0.6792 0.0434
-8.000 -0.3471 0.01189 0.00559 -0.1122 0.6710 0.0438
-7.750 -0.3226 0.01174 0.00538 -0.1114 0.6609 0.0444
-7.500 -0.2977 0.01158 0.00516 -0.1107 0.6519 0.0448
-7.250 -0.2730 0.01145 0.00495 -0.1099 0.6426 0.0453
-7.000 -0.2475 0.01129 0.00474 -0.1092 0.6363 0.0457
-6.750 -0.2217 0.01115 0.00455 -0.1086 0.6310 0.0461
-6.500 -0.1962 0.01099 0.00435 -0.1080 0.6257 0.0466
-6.250 -0.1712 0.01081 0.00413 -0.1072 0.6207 0.0473
-6.000 -0.1449 0.01065 0.00396 -0.1067 0.6173 0.0481
-5.750 -0.1187 0.01051 0.00381 -0.1062 0.6136 0.0488
-5.500 -0.0925 0.01039 0.00366 -0.1057 0.6096 0.0495
-5.250 -0.0666 0.01028 0.00352 -0.1051 0.6052 0.0502
-5.000 -0.0405 0.01018 0.00339 -0.1046 0.6014 0.0509
-4.750 -0.0138 0.01007 0.00325 -0.1041 0.5981 0.0514
-4.500 0.0128 0.00996 0.00313 -0.1037 0.5946 0.0519
-4.250 0.0389 0.00982 0.00298 -0.1031 0.5911 0.0530
-4.000 0.0650 0.00971 0.00286 -0.1026 0.5875 0.0541
-3.750 0.0911 0.00964 0.00277 -0.1020 0.5840 0.0552
-3.500 0.1179 0.00954 0.00268 -0.1016 0.5812 0.0563
-3.250 0.1447 0.00946 0.00258 -0.1012 0.5780 0.0572
-3.000 0.1714 0.00939 0.00250 -0.1007 0.5743 0.0580
-2.750 0.1974 0.00929 0.00240 -0.1002 0.5702 0.0594
-2.500 0.2233 0.00923 0.00233 -0.0996 0.5661 0.0610
-2.250 0.2498 0.00916 0.00226 -0.0991 0.5628 0.0626
-2.000 0.2767 0.00910 0.00220 -0.0987 0.5595 0.0642
-1.750 0.3031 0.00903 0.00214 -0.0982 0.5556 0.0666
-1.500 0.3291 0.00898 0.00209 -0.0977 0.5515 0.0691
-1.250 0.3549 0.00895 0.00205 -0.0970 0.5474 0.0715
-1.000 0.3813 0.00889 0.00201 -0.0966 0.5435 0.0751
-0.750 0.4075 0.00884 0.00197 -0.0961 0.5385 0.0792
-0.500 0.4326 0.00881 0.00194 -0.0953 0.5314 0.0852
-0.250 0.4580 0.00877 0.00193 -0.0947 0.5259 0.0938
0.000 0.4837 0.00872 0.00193 -0.0941 0.5194 0.1051
0.250 0.5082 0.00873 0.00194 -0.0932 0.5118 0.1157
0.500 0.5341 0.00873 0.00195 -0.0927 0.5059 0.1236
0.750 0.5592 0.00874 0.00198 -0.0920 0.4986 0.1316
1.000 0.5840 0.00879 0.00200 -0.0912 0.4914 0.1361
1.250 0.6091 0.00880 0.00203 -0.0905 0.4842 0.1418
1.500 0.6330 0.00886 0.00206 -0.0895 0.4764 0.1466
1.750 0.6581 0.00890 0.00210 -0.0888 0.4698 0.1500
2.000 0.6823 0.00895 0.00214 -0.0880 0.4631 0.1550
2.250 0.7063 0.00900 0.00219 -0.0871 0.4577 0.1602
2.500 0.7310 0.00903 0.00224 -0.0863 0.4522 0.1649
2.750 0.7543 0.00909 0.00230 -0.0853 0.4456 0.1733
3.000 0.7774 0.00915 0.00237 -0.0842 0.4397 0.1842
3.250 0.8009 0.00917 0.00245 -0.0832 0.4339 0.2001
3.500 0.8230 0.00923 0.00253 -0.0820 0.4275 0.2200
3.750 0.8448 0.00926 0.00263 -0.0807 0.4223 0.2508
4.000 0.8661 0.00922 0.00271 -0.0793 0.4183 0.2999
4.250 0.8796 0.00891 0.00285 -0.0764 0.4134 0.4915
4.750 1.0183 0.00874 0.00371 -0.0951 0.3824 0.9833
5.000 1.0497 0.00902 0.00391 -0.0959 0.3696 0.9887
5.250 1.0793 0.00932 0.00413 -0.0965 0.3546 0.9933
5.500 1.1216 0.00965 0.00436 -0.0999 0.3362 0.9977
5.750 1.1569 0.01015 0.00468 -0.1019 0.3043 1.0000
6.000 1.1548 0.01078 0.00509 -0.0961 0.2632 1.0000
6.250 1.1544 0.01120 0.00540 -0.0905 0.2426 1.0000
6.500 1.1600 0.01156 0.00568 -0.0861 0.2282 1.0000
6.750 1.1700 0.01187 0.00595 -0.0827 0.2184 1.0000
7.000 1.1799 0.01223 0.00626 -0.0793 0.2090 1.0000
7.250 1.1947 0.01249 0.00651 -0.0769 0.2044 1.0000
7.500 1.2080 0.01281 0.00681 -0.0743 0.1978 1.0000
7.750 1.2212 0.01318 0.00715 -0.0717 0.1917 1.0000
8.000 1.2374 0.01347 0.00745 -0.0697 0.1883 1.0000
8.250 1.2534 0.01380 0.00777 -0.0678 0.1841 1.0000
8.500 1.2678 0.01420 0.00816 -0.0656 0.1791 1.0000
8.750 1.2826 0.01463 0.00858 -0.0636 0.1741 1.0000
9.000 1.2985 0.01502 0.00898 -0.0618 0.1698 1.0000
9.250 1.3125 0.01553 0.00947 -0.0599 0.1638 1.0000
9.500 1.3263 0.01607 0.01000 -0.0579 0.1582 1.0000
9.750 1.3398 0.01666 0.01057 -0.0561 0.1513 1.0000
10.000 1.3518 0.01736 0.01124 -0.0541 0.1441 1.0000
10.250 1.3623 0.01817 0.01201 -0.0520 0.1355 1.0000
10.500 1.3742 0.01895 0.01278 -0.0503 0.1294 1.0000
10.750 1.3830 0.01994 0.01373 -0.0482 0.1213 1.0000
11.000 1.3933 0.02090 0.01468 -0.0465 0.1141 1.0000
11.250 1.4020 0.02200 0.01576 -0.0447 0.1078 1.0000
11.500 1.4114 0.02309 0.01686 -0.0431 0.1017 1.0000
11.750 1.4186 0.02438 0.01813 -0.0414 0.0946 1.0000
12.000 1.4228 0.02594 0.01965 -0.0396 0.0846 1.0000
12.250 1.4237 0.02778 0.02144 -0.0377 0.0725 1.0000
12.500 1.4253 0.02966 0.02329 -0.0360 0.0645 1.0000
12.750 1.4311 0.03128 0.02492 -0.0347 0.0608 1.0000
13.000 1.4385 0.03280 0.02646 -0.0336 0.0588 1.0000
13.250 1.4445 0.03449 0.02817 -0.0325 0.0568 1.0000
13.500 1.4516 0.03611 0.02982 -0.0316 0.0551 1.0000
13.750 1.4596 0.03769 0.03145 -0.0307 0.0541 1.0000
14.000 1.4667 0.03938 0.03318 -0.0299 0.0533 1.0000
14.250 1.4736 0.04111 0.03494 -0.0291 0.0524 1.0000
14.500 1.4796 0.04295 0.03682 -0.0284 0.0516 1.0000
14.750 1.4845 0.04492 0.03883 -0.0276 0.0508 1.0000
15.000 1.4877 0.04708 0.04102 -0.0269 0.0491 1.0000
15.250 1.4941 0.04896 0.04296 -0.0264 0.0489 1.0000
15.500 1.5016 0.05073 0.04478 -0.0259 0.0484 1.0000
15.750 1.5069 0.05277 0.04687 -0.0254 0.0476 1.0000
16.000 1.5128 0.05475 0.04890 -0.0250 0.0472 1.0000
16.250 1.5168 0.05697 0.05117 -0.0246 0.0465 1.0000
16.500 1.5217 0.05908 0.05334 -0.0242 0.0462 1.0000
16.750 1.5238 0.06155 0.05585 -0.0239 0.0454 1.0000
17.000 1.5267 0.06392 0.05826 -0.0236 0.0446 1.0000
17.250 1.5275 0.06661 0.06099 -0.0235 0.0438 1.0000
17.500 1.5298 0.06911 0.06355 -0.0233 0.0432 1.0000
17.750 1.5331 0.07155 0.06605 -0.0233 0.0428 1.0000
18.000 1.5376 0.07383 0.06839 -0.0232 0.0424 1.0000
18.250 1.5395 0.07648 0.07111 -0.0233 0.0420 1.0000
18.500 1.5428 0.07896 0.07364 -0.0233 0.0414 1.0000
18.750 1.5437 0.08177 0.07652 -0.0235 0.0410 1.0000
19.000 1.5454 0.08445 0.07925 -0.0237 0.0401 1.0000
19.250 1.5448 0.08746 0.08231 -0.0239 0.0395 1.0000
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