GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Reynolds number: 200,000 Max Cl/Cd: 81.92 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe303-il-200000-n5.txt Download as CSV file: xf-goe303-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 303 (FRIEDRICHSHAFEN G03) 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2845 0.12625 0.12251 -0.0387 1.0000 0.0259
-10.750 -0.2843 0.12355 0.11985 -0.0391 1.0000 0.0259
-10.500 -0.2851 0.12092 0.11726 -0.0392 1.0000 0.0260
-10.250 -0.2765 0.11755 0.11393 -0.0376 1.0000 0.0263
-10.000 -0.2730 0.11531 0.11173 -0.0363 1.0000 0.0267
-9.750 -0.2724 0.11350 0.10996 -0.0349 1.0000 0.0274
-9.500 -0.2699 0.11135 0.10784 -0.0347 0.9993 0.0285
-9.250 -0.2578 0.10745 0.10394 -0.0407 0.9952 0.0311
-9.000 -0.2482 0.10347 0.09997 -0.0467 0.9899 0.0313
-8.750 -0.2358 0.09922 0.09571 -0.0524 0.9852 0.0314
-8.500 -0.2243 0.09508 0.09157 -0.0568 0.9782 0.0315
-8.000 -0.1889 0.08799 0.08448 -0.0588 0.9710 0.0328
-7.750 -0.1720 0.08514 0.08163 -0.0616 0.9650 0.0347
-7.500 -0.1572 0.08071 0.07718 -0.0727 0.9527 0.0380
-7.250 -0.1368 0.07578 0.07221 -0.0811 0.9439 0.0382
-7.000 -0.1137 0.07087 0.06724 -0.0880 0.9369 0.0383
-6.500 -0.0812 0.06486 0.06122 -0.0893 0.9233 0.0398
-6.250 -0.0592 0.06237 0.05870 -0.0917 0.9165 0.0421
-6.000 -0.0327 0.05592 0.05209 -0.1004 0.9068 0.0368
-5.750 -0.0086 0.05182 0.04788 -0.1047 0.8982 0.0356
-5.500 0.0204 0.04718 0.04306 -0.1103 0.8896 0.0364
-5.250 0.0479 0.04271 0.03839 -0.1146 0.8800 0.0365
-5.000 0.0773 0.03829 0.03372 -0.1184 0.8718 0.0361
-4.750 0.1049 0.03394 0.02907 -0.1211 0.8614 0.0362
-4.500 0.1351 0.02841 0.02299 -0.1239 0.8525 0.0373
-4.250 0.1624 0.02446 0.01852 -0.1251 0.8424 0.0374
-4.000 0.1897 0.02159 0.01510 -0.1256 0.8318 0.0377
-3.750 0.2177 0.01974 0.01275 -0.1258 0.8213 0.0385
-3.500 0.2448 0.01857 0.01139 -0.1258 0.8096 0.0394
-3.250 0.2721 0.01762 0.01021 -0.1257 0.7971 0.0400
-3.000 0.2999 0.01674 0.00909 -0.1256 0.7848 0.0405
-2.750 0.3277 0.01600 0.00814 -0.1254 0.7725 0.0411
-2.500 0.3555 0.01538 0.00732 -0.1252 0.7603 0.0418
-2.250 0.3831 0.01485 0.00662 -0.1250 0.7480 0.0426
-2.000 0.4106 0.01442 0.00605 -0.1247 0.7360 0.0437
-1.750 0.4381 0.01411 0.00560 -0.1245 0.7245 0.0454
-1.500 0.4656 0.01381 0.00517 -0.1242 0.7138 0.0466
-1.250 0.4927 0.01347 0.00480 -0.1239 0.7026 0.0479
-1.000 0.5199 0.01327 0.00455 -0.1237 0.6922 0.0495
-0.750 0.5471 0.01313 0.00433 -0.1234 0.6816 0.0516
-0.500 0.5742 0.01300 0.00414 -0.1231 0.6696 0.0543
-0.250 0.6011 0.01290 0.00400 -0.1228 0.6575 0.0586
0.000 0.6279 0.01284 0.00390 -0.1225 0.6459 0.0675
0.250 0.6547 0.01277 0.00383 -0.1222 0.6345 0.0845
0.500 0.6815 0.01272 0.00380 -0.1220 0.6233 0.1083
0.750 0.7081 0.01269 0.00381 -0.1217 0.6120 0.1378
1.250 0.7613 0.01101 0.00396 -0.1213 0.5879 1.0000
2.000 0.8410 0.01148 0.00409 -0.1203 0.5602 1.0000
2.250 0.8674 0.01167 0.00416 -0.1199 0.5518 1.0000
2.500 0.8938 0.01183 0.00426 -0.1196 0.5428 1.0000
2.750 0.9199 0.01201 0.00438 -0.1192 0.5339 1.0000
3.000 0.9458 0.01220 0.00450 -0.1188 0.5240 1.0000
3.250 0.9716 0.01239 0.00463 -0.1184 0.5140 1.0000
3.500 0.9970 0.01261 0.00478 -0.1179 0.5039 1.0000
3.750 1.0226 0.01280 0.00495 -0.1175 0.4933 1.0000
4.000 1.0479 0.01302 0.00513 -0.1170 0.4829 1.0000
4.250 1.0727 0.01325 0.00532 -0.1164 0.4721 1.0000
4.500 1.0975 0.01348 0.00553 -0.1159 0.4602 1.0000
4.750 1.1220 0.01373 0.00575 -0.1153 0.4476 1.0000
5.000 1.1460 0.01399 0.00599 -0.1146 0.4342 1.0000
5.250 1.1693 0.01429 0.00624 -0.1138 0.4193 1.0000
5.500 1.1921 0.01461 0.00652 -0.1129 0.4028 1.0000
5.750 1.2142 0.01497 0.00683 -0.1120 0.3855 1.0000
6.000 1.2359 0.01535 0.00716 -0.1110 0.3688 1.0000
6.250 1.2570 0.01577 0.00753 -0.1099 0.3526 1.0000
6.500 1.2778 0.01621 0.00793 -0.1087 0.3374 1.0000
6.750 1.2981 0.01667 0.00836 -0.1075 0.3237 1.0000
7.000 1.3175 0.01718 0.00882 -0.1062 0.3095 1.0000
7.250 1.3361 0.01772 0.00930 -0.1048 0.2958 1.0000
7.500 1.3543 0.01828 0.00983 -0.1033 0.2842 1.0000
7.750 1.3727 0.01881 0.01035 -0.1019 0.2747 1.0000
8.000 1.3911 0.01933 0.01089 -0.1004 0.2660 1.0000
8.250 1.4077 0.01992 0.01146 -0.0987 0.2579 1.0000
8.500 1.4246 0.02043 0.01203 -0.0970 0.2505 1.0000
8.750 1.4394 0.02102 0.01263 -0.0950 0.2434 1.0000
9.000 1.4551 0.02160 0.01326 -0.0932 0.2380 1.0000
9.250 1.4719 0.02214 0.01389 -0.0916 0.2327 1.0000
9.500 1.4864 0.02281 0.01461 -0.0898 0.2272 1.0000
9.750 1.5014 0.02346 0.01533 -0.0880 0.2219 1.0000
10.000 1.5165 0.02410 0.01607 -0.0864 0.2154 1.0000
10.250 1.5276 0.02497 0.01695 -0.0843 0.2089 1.0000
10.500 1.5427 0.02564 0.01776 -0.0827 0.2005 1.0000
10.750 1.5533 0.02656 0.01873 -0.0808 0.1913 1.0000
11.000 1.5639 0.02752 0.01974 -0.0789 0.1797 1.0000
11.250 1.5743 0.02855 0.02083 -0.0771 0.1660 1.0000
11.500 1.5822 0.02979 0.02208 -0.0752 0.1492 1.0000
11.750 1.5850 0.03146 0.02368 -0.0731 0.1294 1.0000
12.000 1.5845 0.03350 0.02564 -0.0708 0.1130 1.0000
12.500 1.5857 0.03770 0.02986 -0.0670 0.0929 1.0000
12.750 1.5857 0.03998 0.03219 -0.0654 0.0861 1.0000
13.000 1.5854 0.04240 0.03466 -0.0640 0.0795 1.0000
13.250 1.5853 0.04488 0.03723 -0.0629 0.0742 1.0000
13.500 1.5858 0.04739 0.03983 -0.0619 0.0692 1.0000
13.750 1.5831 0.05032 0.04284 -0.0610 0.0647 1.0000
14.000 1.5834 0.05300 0.04565 -0.0603 0.0595 1.0000
14.250 1.5788 0.05636 0.04906 -0.0598 0.0547 1.0000
14.500 1.5768 0.05950 0.05232 -0.0595 0.0490 1.0000
14.750 1.5714 0.06317 0.05606 -0.0593 0.0437 1.0000
15.000 1.5641 0.06717 0.06013 -0.0594 0.0382 1.0000
15.250 1.5560 0.07138 0.06442 -0.0596 0.0328 1.0000
15.500 1.5461 0.07597 0.06908 -0.0601 0.0287 1.0000
15.750 1.5349 0.08085 0.07404 -0.0608 0.0259 1.0000
16.000 1.5241 0.08578 0.07908 -0.0616 0.0239 1.0000
16.250 1.5124 0.09099 0.08439 -0.0627 0.0224 1.0000
16.500 1.4999 0.09645 0.08995 -0.0640 0.0213 1.0000
16.750 1.4889 0.10175 0.09540 -0.0654 0.0204 1.0000
17.000 1.4774 0.10723 0.10101 -0.0670 0.0196 1.0000
17.250 1.4654 0.11293 0.10684 -0.0689 0.0190 1.0000
17.500 1.4534 0.11872 0.11276 -0.0710 0.0185 1.0000
17.750 1.4409 0.12473 0.11889 -0.0733 0.0180 1.0000
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Polar data table (+)
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