GOE 480 AIRFOIL (goe480-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 480 AIRFOIL (goe480-il) Reynolds number: 200,000 Max Cl/Cd: 79.21 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe480-il-200000-n5.txt Download as CSV file: xf-goe480-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2723 0.11693 0.11308 -0.0445 1.0000 0.0376
-11.000 -0.2763 0.11360 0.10979 -0.0451 1.0000 0.0380
-10.750 -0.2762 0.11132 0.10756 -0.0446 1.0000 0.0389
-10.500 -0.2612 0.10855 0.10480 -0.0467 0.9975 0.0396
-10.250 -0.2441 0.10546 0.10171 -0.0500 0.9909 0.0414
-10.000 -0.2315 0.10132 0.09755 -0.0542 0.9843 0.0423
-9.750 -0.2214 0.09698 0.09320 -0.0584 0.9756 0.0430
-9.500 -0.2150 0.09191 0.08812 -0.0643 0.9660 0.0449
-9.250 -0.1891 0.09021 0.08641 -0.0660 0.9599 0.0466
-9.000 -0.1720 0.08653 0.08270 -0.0705 0.9508 0.0476
-8.750 -0.1559 0.08216 0.07830 -0.0759 0.9406 0.0477
-8.500 -0.1387 0.07782 0.07392 -0.0818 0.9292 0.0485
-8.250 -0.1235 0.07300 0.06904 -0.0888 0.9148 0.0497
-8.000 -0.1140 0.06799 0.06396 -0.0955 0.8967 0.0502
-7.750 -0.1099 0.06239 0.05826 -0.1027 0.8779 0.0507
-7.500 -0.1124 0.05421 0.04990 -0.1123 0.8596 0.0519
-7.250 -0.0924 0.05371 0.04935 -0.1117 0.8497 0.0526
-7.000 -0.0826 0.04968 0.04518 -0.1148 0.8374 0.0528
-6.750 -0.0723 0.04527 0.04060 -0.1178 0.8269 0.0531
-6.500 -0.0573 0.04218 0.03732 -0.1194 0.8178 0.0537
-6.250 -0.0416 0.03941 0.03438 -0.1205 0.8091 0.0547
-6.000 -0.0285 0.03471 0.02932 -0.1221 0.8010 0.0552
-5.750 -0.0141 0.03067 0.02486 -0.1227 0.7935 0.0556
-5.500 0.0038 0.02789 0.02168 -0.1227 0.7862 0.0562
-5.250 0.0247 0.02586 0.01927 -0.1225 0.7801 0.0573
-5.000 0.0458 0.02416 0.01724 -0.1220 0.7729 0.0580
-4.750 0.0688 0.02274 0.01549 -0.1215 0.7666 0.0584
-4.500 0.0927 0.02159 0.01405 -0.1210 0.7606 0.0588
-4.250 0.1168 0.02064 0.01286 -0.1205 0.7538 0.0592
-4.000 0.1422 0.01984 0.01181 -0.1200 0.7480 0.0596
-3.750 0.1676 0.01925 0.01101 -0.1195 0.7418 0.0601
-3.500 0.1926 0.01844 0.01003 -0.1190 0.7352 0.0609
-3.250 0.2185 0.01771 0.00918 -0.1187 0.7297 0.0617
-3.000 0.2441 0.01715 0.00856 -0.1183 0.7232 0.0623
-2.750 0.2700 0.01667 0.00800 -0.1178 0.7167 0.0628
-2.500 0.2968 0.01625 0.00747 -0.1175 0.7112 0.0634
-2.250 0.3225 0.01587 0.00706 -0.1169 0.7042 0.0641
-2.000 0.3487 0.01552 0.00665 -0.1165 0.6977 0.0648
-1.750 0.3753 0.01521 0.00627 -0.1161 0.6919 0.0655
-1.500 0.4010 0.01492 0.00598 -0.1155 0.6845 0.0664
-1.250 0.4274 0.01469 0.00570 -0.1151 0.6781 0.0678
-1.000 0.4534 0.01449 0.00547 -0.1146 0.6713 0.0691
-0.750 0.4793 0.01429 0.00525 -0.1140 0.6638 0.0701
-0.500 0.5056 0.01412 0.00503 -0.1136 0.6574 0.0709
-0.250 0.5309 0.01392 0.00485 -0.1129 0.6493 0.0718
0.000 0.5566 0.01371 0.00462 -0.1124 0.6423 0.0733
0.250 0.5820 0.01357 0.00451 -0.1118 0.6344 0.0749
0.500 0.6078 0.01347 0.00439 -0.1113 0.6266 0.0768
0.750 0.6334 0.01341 0.00432 -0.1107 0.6186 0.0792
1.000 0.6590 0.01336 0.00425 -0.1101 0.6103 0.0827
1.250 0.6844 0.01331 0.00421 -0.1095 0.6019 0.0878
1.500 0.7097 0.01326 0.00418 -0.1088 0.5933 0.0958
1.750 0.7345 0.01315 0.00423 -0.1082 0.5846 0.1342
2.000 0.7591 0.01306 0.00429 -0.1075 0.5759 0.2039
2.250 0.7816 0.01272 0.00442 -0.1066 0.5671 0.3691
2.750 0.8618 0.01178 0.00467 -0.1117 0.5466 1.0000
3.000 0.8856 0.01195 0.00474 -0.1108 0.5376 1.0000
3.250 0.9093 0.01213 0.00486 -0.1098 0.5281 1.0000
3.500 0.9329 0.01232 0.00498 -0.1089 0.5191 1.0000
3.750 0.9564 0.01251 0.00511 -0.1080 0.5100 1.0000
4.000 0.9799 0.01271 0.00527 -0.1071 0.5015 1.0000
4.250 1.0031 0.01293 0.00543 -0.1061 0.4928 1.0000
4.500 1.0262 0.01314 0.00562 -0.1052 0.4842 1.0000
4.750 1.0489 0.01338 0.00581 -0.1042 0.4752 1.0000
5.000 1.0718 0.01361 0.00602 -0.1032 0.4668 1.0000
5.250 1.0941 0.01386 0.00625 -0.1021 0.4582 1.0000
5.500 1.1165 0.01410 0.00649 -0.1011 0.4497 1.0000
5.750 1.1379 0.01438 0.00673 -0.0999 0.4406 1.0000
6.000 1.1597 0.01464 0.00700 -0.0988 0.4318 1.0000
6.250 1.1807 0.01493 0.00728 -0.0975 0.4236 1.0000
6.500 1.2019 0.01521 0.00758 -0.0963 0.4151 1.0000
6.750 1.2217 0.01554 0.00788 -0.0949 0.4063 1.0000
7.000 1.2415 0.01584 0.00821 -0.0935 0.3964 1.0000
7.250 1.2595 0.01620 0.00855 -0.0918 0.3863 1.0000
7.500 1.2771 0.01655 0.00891 -0.0900 0.3755 1.0000
7.750 1.2941 0.01693 0.00929 -0.0882 0.3650 1.0000
8.000 1.3080 0.01734 0.00967 -0.0858 0.3548 1.0000
8.250 1.3228 0.01774 0.01010 -0.0836 0.3444 1.0000
8.500 1.3367 0.01819 0.01056 -0.0813 0.3352 1.0000
8.750 1.3502 0.01867 0.01105 -0.0790 0.3256 1.0000
9.000 1.3637 0.01917 0.01157 -0.0768 0.3160 1.0000
9.500 1.3872 0.02036 0.01279 -0.0721 0.2951 1.0000
9.750 1.3971 0.02107 0.01349 -0.0697 0.2831 1.0000
10.000 1.4054 0.02188 0.01428 -0.0672 0.2706 1.0000
10.250 1.4122 0.02282 0.01519 -0.0646 0.2571 1.0000
10.500 1.4193 0.02381 0.01618 -0.0623 0.2438 1.0000
10.750 1.4282 0.02478 0.01718 -0.0603 0.2322 1.0000
11.000 1.4352 0.02591 0.01831 -0.0582 0.2203 1.0000
11.250 1.4407 0.02718 0.01958 -0.0561 0.2079 1.0000
11.500 1.4451 0.02860 0.02099 -0.0542 0.1945 1.0000
11.750 1.4484 0.03018 0.02255 -0.0523 0.1789 1.0000
12.000 1.4492 0.03202 0.02437 -0.0504 0.1600 1.0000
12.250 1.4458 0.03429 0.02655 -0.0485 0.1385 1.0000
12.500 1.4399 0.03690 0.02906 -0.0467 0.1165 1.0000
12.750 1.4326 0.03976 0.03182 -0.0451 0.0990 1.0000
13.000 1.4272 0.04258 0.03461 -0.0438 0.0874 1.0000
13.250 1.4243 0.04527 0.03732 -0.0427 0.0797 1.0000
13.500 1.4207 0.04815 0.04023 -0.0418 0.0736 1.0000
13.750 1.4186 0.05097 0.04312 -0.0412 0.0685 1.0000
14.000 1.4144 0.05413 0.04634 -0.0406 0.0644 1.0000
14.250 1.4136 0.05702 0.04932 -0.0403 0.0605 1.0000
14.500 1.4095 0.06040 0.05276 -0.0401 0.0572 1.0000
14.750 1.4060 0.06378 0.05623 -0.0401 0.0542 1.0000
15.000 1.4041 0.06709 0.05964 -0.0402 0.0511 1.0000
15.250 1.3992 0.07086 0.06349 -0.0405 0.0485 1.0000
15.500 1.3951 0.07461 0.06732 -0.0409 0.0461 1.0000
15.750 1.3925 0.07822 0.07105 -0.0414 0.0437 1.0000
16.000 1.3879 0.08219 0.07511 -0.0421 0.0416 1.0000
16.250 1.3812 0.08656 0.07954 -0.0430 0.0399 1.0000
16.500 1.3783 0.09040 0.08350 -0.0438 0.0381 1.0000
16.750 1.3747 0.09440 0.08761 -0.0448 0.0365 1.0000
17.000 1.3702 0.09862 0.09190 -0.0459 0.0350 1.0000
17.250 1.3639 0.10317 0.09651 -0.0472 0.0338 1.0000
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