GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Reynolds number: 1,000,000 Max Cl/Cd: 138.2 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe301-il-1000000.txt Download as CSV file: xf-goe301-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 301 (FRIEDRICHSHAFEN G 13) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1478 0.08678 0.08513 -0.0657 0.9831 0.0187
-8.250 -0.1367 0.08251 0.08087 -0.0684 0.9752 0.0189
-8.000 -0.1203 0.07993 0.07829 -0.0700 0.9664 0.0190
-7.750 -0.1018 0.07719 0.07554 -0.0731 0.9543 0.0193
-7.500 -0.0817 0.07428 0.07258 -0.0771 0.9364 0.0197
-7.250 -0.0634 0.07134 0.06955 -0.0810 0.9140 0.0204
-6.750 -0.0232 0.05985 0.05781 -0.0997 0.8684 0.0224
-6.500 -0.0075 0.05792 0.05578 -0.1001 0.8427 0.0226
-6.250 0.0100 0.05602 0.05373 -0.1014 0.8071 0.0229
-6.000 0.0293 0.05397 0.05149 -0.1035 0.7694 0.0233
-5.750 0.0514 0.05154 0.04890 -0.1065 0.7429 0.0240
-5.500 0.0958 0.04430 0.04138 -0.1187 0.7263 0.0262
-5.250 0.1156 0.04062 0.03758 -0.1213 0.7127 0.0267
-5.000 0.1385 0.03913 0.03601 -0.1223 0.7012 0.0270
-4.500 0.1906 0.03537 0.03204 -0.1256 0.6828 0.0286
-4.250 0.2298 0.02807 0.02431 -0.1313 0.6760 0.0312
-4.000 0.2551 0.02690 0.02307 -0.1319 0.6684 0.0316
-3.750 0.2809 0.02584 0.02191 -0.1324 0.6605 0.0320
-3.500 0.3146 0.01488 0.00979 -0.1353 0.6560 0.0310
-3.250 0.3420 0.01305 0.00767 -0.1356 0.6493 0.0316
-3.000 0.3695 0.01311 0.00770 -0.1355 0.6424 0.0322
-2.750 0.3976 0.01245 0.00693 -0.1355 0.6362 0.0327
-2.500 0.4255 0.01148 0.00574 -0.1355 0.6294 0.0331
-2.250 0.4532 0.01085 0.00496 -0.1354 0.6227 0.0336
-2.000 0.4814 0.01035 0.00435 -0.1354 0.6160 0.0341
-1.750 0.5091 0.01000 0.00389 -0.1353 0.6091 0.0348
-1.500 0.5373 0.00974 0.00358 -0.1352 0.6024 0.0355
-1.250 0.5651 0.00968 0.00345 -0.1351 0.5946 0.0360
-1.000 0.5927 0.00910 0.00281 -0.1350 0.5864 0.0372
-0.750 0.6202 0.00899 0.00265 -0.1348 0.5761 0.0381
-0.500 0.6481 0.00889 0.00253 -0.1347 0.5649 0.0390
-0.250 0.6757 0.00883 0.00242 -0.1346 0.5540 0.0402
0.000 0.7031 0.00879 0.00232 -0.1344 0.5426 0.0414
0.250 0.7306 0.00872 0.00219 -0.1342 0.5291 0.0429
0.500 0.7579 0.00870 0.00213 -0.1341 0.5146 0.0453
0.750 0.7852 0.00874 0.00213 -0.1339 0.5006 0.0477
1.000 0.8123 0.00881 0.00214 -0.1337 0.4873 0.0497
1.250 0.8394 0.00882 0.00211 -0.1335 0.4741 0.0544
1.500 0.8662 0.00893 0.00217 -0.1332 0.4617 0.0581
1.750 0.8934 0.00897 0.00219 -0.1331 0.4511 0.0644
2.000 0.9205 0.00907 0.00226 -0.1329 0.4419 0.0689
2.250 0.9474 0.00913 0.00229 -0.1327 0.4328 0.0759
2.500 0.9747 0.00919 0.00234 -0.1326 0.4256 0.0811
2.750 1.0016 0.00926 0.00241 -0.1324 0.4182 0.0921
3.000 1.0291 0.00877 0.00265 -0.1328 0.4119 0.4819
3.250 1.0522 0.00792 0.00283 -0.1319 0.4057 1.0000
3.500 1.0788 0.00809 0.00294 -0.1316 0.3989 1.0000
3.750 1.1060 0.00821 0.00303 -0.1315 0.3925 1.0000
4.000 1.1324 0.00838 0.00315 -0.1312 0.3853 1.0000
4.250 1.1594 0.00851 0.00326 -0.1311 0.3795 1.0000
4.500 1.1859 0.00866 0.00338 -0.1309 0.3725 1.0000
4.750 1.2122 0.00884 0.00352 -0.1306 0.3656 1.0000
5.000 1.2388 0.00898 0.00364 -0.1304 0.3586 1.0000
5.250 1.2646 0.00918 0.00380 -0.1301 0.3509 1.0000
5.500 1.2908 0.00934 0.00394 -0.1298 0.3426 1.0000
5.750 1.3163 0.00955 0.00411 -0.1295 0.3341 1.0000
6.000 1.3418 0.00975 0.00429 -0.1291 0.3241 1.0000
6.250 1.3672 0.00996 0.00447 -0.1288 0.3150 1.0000
6.500 1.3918 0.01022 0.00468 -0.1283 0.3050 1.0000
6.750 1.4167 0.01045 0.00489 -0.1278 0.2950 1.0000
7.000 1.4410 0.01071 0.00512 -0.1273 0.2851 1.0000
7.250 1.4646 0.01102 0.00538 -0.1267 0.2744 1.0000
7.500 1.4877 0.01135 0.00565 -0.1260 0.2621 1.0000
7.750 1.5106 0.01168 0.00595 -0.1252 0.2499 1.0000
8.000 1.5331 0.01203 0.00626 -0.1245 0.2389 1.0000
8.250 1.5547 0.01243 0.00660 -0.1235 0.2264 1.0000
8.500 1.5756 0.01286 0.00697 -0.1225 0.2138 1.0000
8.750 1.5966 0.01326 0.00733 -0.1215 0.2030 1.0000
9.000 1.6175 0.01364 0.00769 -0.1204 0.1919 1.0000
9.250 1.6366 0.01413 0.00811 -0.1191 0.1780 1.0000
9.500 1.6522 0.01479 0.00866 -0.1172 0.1585 1.0000
9.750 1.6667 0.01543 0.00922 -0.1151 0.1424 1.0000
10.000 1.6799 0.01605 0.00978 -0.1127 0.1318 1.0000
10.250 1.6946 0.01660 0.01031 -0.1107 0.1251 1.0000
10.500 1.7084 0.01720 0.01091 -0.1085 0.1186 1.0000
10.750 1.7240 0.01771 0.01144 -0.1067 0.1144 1.0000
11.000 1.7366 0.01839 0.01212 -0.1045 0.1087 1.0000
11.250 1.7514 0.01896 0.01272 -0.1027 0.1039 1.0000
11.500 1.7629 0.01973 0.01348 -0.1005 0.0966 1.0000
11.750 1.7721 0.02065 0.01437 -0.0980 0.0840 1.0000
12.000 1.7596 0.02298 0.01645 -0.0930 0.0520 1.0000
12.250 1.7539 0.02507 0.01848 -0.0893 0.0376 1.0000
12.500 1.7487 0.02728 0.02063 -0.0861 0.0253 1.0000
12.750 1.7487 0.02925 0.02262 -0.0837 0.0201 1.0000
13.000 1.7499 0.03123 0.02464 -0.0817 0.0177 1.0000
13.250 1.7538 0.03308 0.02657 -0.0801 0.0164 1.0000
13.500 1.7564 0.03517 0.02873 -0.0787 0.0155 1.0000
13.750 1.7563 0.03761 0.03124 -0.0774 0.0146 1.0000
14.000 1.7546 0.04035 0.03407 -0.0763 0.0139 1.0000
14.250 1.7567 0.04278 0.03659 -0.0755 0.0135 1.0000
14.500 1.7572 0.04544 0.03935 -0.0748 0.0131 1.0000
14.750 1.7558 0.04838 0.04238 -0.0742 0.0127 1.0000
15.000 1.7525 0.05161 0.04571 -0.0738 0.0124 1.0000
15.250 1.7477 0.05511 0.04929 -0.0734 0.0120 1.0000
15.500 1.7392 0.05910 0.05339 -0.0732 0.0117 1.0000
15.750 1.7278 0.06359 0.05799 -0.0731 0.0114 1.0000
16.000 1.7135 0.06860 0.06312 -0.0733 0.0111 1.0000
16.250 1.7079 0.07251 0.06714 -0.0735 0.0110 1.0000
16.500 1.7008 0.07671 0.07144 -0.0739 0.0108 1.0000
16.750 1.6925 0.08115 0.07599 -0.0745 0.0107 1.0000
17.000 1.6830 0.08586 0.08080 -0.0752 0.0105 1.0000
17.250 1.6731 0.09066 0.08571 -0.0760 0.0103 1.0000
17.500 1.6625 0.09563 0.09079 -0.0770 0.0101 1.0000
17.750 1.6506 0.10087 0.09613 -0.0781 0.0100 1.0000
18.000 1.6391 0.10612 0.10148 -0.0794 0.0098 1.0000
18.250 1.6273 0.11142 0.10688 -0.0808 0.0097 1.0000
18.500 1.6146 0.11692 0.11248 -0.0824 0.0096 1.0000
18.750 1.6020 0.12248 0.11814 -0.0842 0.0094 1.0000
19.000 1.5893 0.12816 0.12392 -0.0862 0.0093 1.0000
19.250 1.5764 0.13395 0.12980 -0.0884 0.0092 1.0000
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