GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Reynolds number: 200,000 Max Cl/Cd: 86.12 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe304-il-200000-n5.txt Download as CSV file: xf-goe304-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 304 (FRIEDRICHSHAFEN G02) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1391 0.09113 0.08743 -0.0601 0.9626 0.0353
-7.750 -0.1254 0.08805 0.08434 -0.0650 0.9513 0.0365
-7.500 -0.1122 0.08498 0.08125 -0.0728 0.9367 0.0368
-7.250 -0.0935 0.08127 0.07752 -0.0766 0.9287 0.0370
-7.000 -0.0796 0.07825 0.07449 -0.0763 0.9191 0.0373
-6.750 -0.0623 0.07529 0.07152 -0.0783 0.9104 0.0377
-6.500 -0.0459 0.07253 0.06873 -0.0808 0.8991 0.0382
-6.250 -0.0280 0.06973 0.06589 -0.0838 0.8881 0.0389
-6.000 -0.0076 0.06677 0.06287 -0.0876 0.8781 0.0399
-5.750 0.0268 0.06288 0.05882 -0.0993 0.8652 0.0418
-5.500 0.0537 0.05921 0.05505 -0.1050 0.8549 0.0420
-5.250 0.0692 0.05665 0.05246 -0.1045 0.8459 0.0423
-5.000 0.0878 0.05426 0.05003 -0.1053 0.8358 0.0427
-4.750 0.1108 0.05179 0.04747 -0.1073 0.8268 0.0434
-4.500 0.1358 0.04927 0.04487 -0.1101 0.8167 0.0443
-4.250 0.1644 0.04659 0.04206 -0.1135 0.8078 0.0456
-4.000 0.2154 0.04226 0.03728 -0.1230 0.7984 0.0477
-3.750 0.2323 0.04018 0.03523 -0.1225 0.7897 0.0482
-3.500 0.2548 0.03839 0.03339 -0.1230 0.7804 0.0490
-3.250 0.2819 0.03637 0.03124 -0.1245 0.7718 0.0498
-2.750 0.3500 0.02956 0.02376 -0.1296 0.7556 0.0415
-2.500 0.3769 0.02784 0.02190 -0.1303 0.7471 0.0408
-2.250 0.4067 0.02579 0.01958 -0.1312 0.7397 0.0406
-2.000 0.4372 0.02362 0.01706 -0.1319 0.7315 0.0412
-1.500 0.4948 0.02047 0.01337 -0.1325 0.7164 0.0407
-1.250 0.5238 0.01907 0.01163 -0.1326 0.7091 0.0407
-1.000 0.5525 0.01787 0.01012 -0.1326 0.7016 0.0411
-0.750 0.5809 0.01696 0.00887 -0.1325 0.6941 0.0422
-0.500 0.6081 0.01658 0.00848 -0.1324 0.6868 0.0434
-0.250 0.6357 0.01607 0.00783 -0.1322 0.6790 0.0444
0.000 0.6635 0.01554 0.00711 -0.1319 0.6722 0.0451
0.250 0.6910 0.01508 0.00655 -0.1317 0.6643 0.0460
0.500 0.7185 0.01472 0.00603 -0.1314 0.6572 0.0470
0.750 0.7456 0.01443 0.00572 -0.1311 0.6495 0.0487
1.000 0.7726 0.01424 0.00554 -0.1308 0.6419 0.0510
1.250 0.7996 0.01404 0.00530 -0.1305 0.6343 0.0527
1.500 0.8265 0.01389 0.00511 -0.1301 0.6262 0.0543
1.750 0.8531 0.01369 0.00496 -0.1298 0.6177 0.0565
2.000 0.8791 0.01363 0.00487 -0.1294 0.6058 0.0604
2.250 0.9048 0.01354 0.00478 -0.1288 0.5916 0.0639
2.500 0.9306 0.01352 0.00474 -0.1283 0.5784 0.0680
2.750 0.9565 0.01354 0.00474 -0.1278 0.5674 0.0749
3.000 0.9823 0.01358 0.00477 -0.1273 0.5553 0.0839
3.250 1.0080 0.01357 0.00485 -0.1268 0.5427 0.1164
3.750 1.0567 0.01246 0.00513 -0.1254 0.5183 1.0000
4.000 1.0818 0.01267 0.00526 -0.1248 0.5057 1.0000
4.250 1.1067 0.01289 0.00542 -0.1242 0.4929 1.0000
4.500 1.1311 0.01314 0.00559 -0.1235 0.4792 1.0000
4.750 1.1549 0.01341 0.00578 -0.1227 0.4641 1.0000
5.000 1.1781 0.01372 0.00600 -0.1218 0.4477 1.0000
5.250 1.2009 0.01405 0.00624 -0.1208 0.4307 1.0000
5.500 1.2234 0.01440 0.00652 -0.1199 0.4142 1.0000
5.750 1.2457 0.01477 0.00682 -0.1189 0.3981 1.0000
6.000 1.2674 0.01516 0.00715 -0.1178 0.3811 1.0000
6.250 1.2884 0.01558 0.00750 -0.1167 0.3629 1.0000
6.500 1.3090 0.01603 0.00788 -0.1155 0.3450 1.0000
6.750 1.3287 0.01652 0.00831 -0.1142 0.3263 1.0000
7.000 1.3469 0.01708 0.00877 -0.1126 0.3062 1.0000
7.250 1.3645 0.01767 0.00927 -0.1110 0.2872 1.0000
7.500 1.3819 0.01826 0.00981 -0.1094 0.2711 1.0000
8.000 1.4154 0.01946 0.01094 -0.1060 0.2443 1.0000
8.250 1.4303 0.02007 0.01154 -0.1040 0.2335 1.0000
8.500 1.4438 0.02075 0.01221 -0.1018 0.2238 1.0000
8.750 1.4583 0.02140 0.01288 -0.0999 0.2142 1.0000
9.000 1.4717 0.02214 0.01361 -0.0978 0.2056 1.0000
9.250 1.4846 0.02291 0.01440 -0.0958 0.1967 1.0000
9.500 1.4977 0.02370 0.01523 -0.0938 0.1886 1.0000
9.750 1.5095 0.02459 0.01613 -0.0918 0.1806 1.0000
10.000 1.5218 0.02547 0.01705 -0.0900 0.1731 1.0000
10.250 1.5323 0.02649 0.01809 -0.0880 0.1650 1.0000
10.500 1.5434 0.02750 0.01915 -0.0862 0.1571 1.0000
10.750 1.5519 0.02873 0.02039 -0.0843 0.1490 1.0000
11.000 1.5625 0.02985 0.02157 -0.0826 0.1409 1.0000
11.250 1.5696 0.03126 0.02299 -0.0808 0.1339 1.0000
11.500 1.5794 0.03252 0.02432 -0.0793 0.1272 1.0000
12.000 1.5936 0.03557 0.02746 -0.0762 0.1150 1.0000
12.250 1.5984 0.03736 0.02926 -0.0747 0.1095 1.0000
12.500 1.6048 0.03906 0.03103 -0.0734 0.1050 1.0000
12.750 1.6097 0.04093 0.03296 -0.0721 0.1007 1.0000
13.000 1.6120 0.04309 0.03515 -0.0708 0.0972 1.0000
13.250 1.6171 0.04504 0.03721 -0.0697 0.0941 1.0000
13.500 1.6209 0.04713 0.03940 -0.0687 0.0910 1.0000
13.750 1.6225 0.04951 0.04185 -0.0677 0.0880 1.0000
14.000 1.6211 0.05228 0.04466 -0.0669 0.0853 1.0000
14.250 1.6254 0.05449 0.04701 -0.0662 0.0825 1.0000
14.500 1.6282 0.05691 0.04957 -0.0655 0.0795 1.0000
14.750 1.6278 0.05976 0.05251 -0.0650 0.0765 1.0000
15.000 1.6238 0.06312 0.05592 -0.0647 0.0738 1.0000
15.250 1.6284 0.06551 0.05849 -0.0644 0.0702 1.0000
15.500 1.6289 0.06844 0.06155 -0.0642 0.0663 1.0000
15.750 1.6265 0.07182 0.06502 -0.0642 0.0627 1.0000
16.000 1.6275 0.07482 0.06817 -0.0643 0.0574 1.0000
16.250 1.6243 0.07844 0.07188 -0.0646 0.0525 1.0000
16.750 1.6112 0.08683 0.08040 -0.0657 0.0442 1.0000
17.000 1.6014 0.09165 0.08527 -0.0667 0.0415 1.0000
17.250 1.5920 0.09648 0.09020 -0.0677 0.0393 1.0000
17.500 1.5816 0.10158 0.09540 -0.0690 0.0374 1.0000
17.750 1.5693 0.10705 0.10097 -0.0706 0.0360 1.0000
18.000 1.5574 0.11257 0.10660 -0.0724 0.0348 1.0000
18.250 1.5474 0.11786 0.11203 -0.0742 0.0335 1.0000
18.500 1.5364 0.12343 0.11773 -0.0764 0.0324 1.0000
18.750 1.5245 0.12924 0.12365 -0.0788 0.0315 1.0000
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