GOE 342 AIRFOIL (goe342-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 342 AIRFOIL (goe342-il) Reynolds number: 100,000 Max Cl/Cd: 71.42 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe342-il-100000-n5.txt Download as CSV file: xf-goe342-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 342 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2787 0.10742 0.10261 -0.0295 1.0000 0.0293
-8.000 -0.2837 0.10606 0.10134 -0.0277 1.0000 0.0298
-7.750 -0.2926 0.10515 0.10051 -0.0251 1.0000 0.0302
-7.500 -0.2910 0.10339 0.09880 -0.0256 0.9968 0.0309
-7.250 -0.2687 0.10060 0.09601 -0.0331 0.9880 0.0318
-7.000 -0.2358 0.09849 0.09386 -0.0464 0.9781 0.0324
-6.750 -0.2024 0.09545 0.09076 -0.0577 0.9700 0.0326
-6.500 -0.1974 0.08873 0.08410 -0.0531 0.9683 0.0334
-6.250 -0.1824 0.08454 0.07991 -0.0537 0.9631 0.0342
-6.000 -0.1594 0.08075 0.07610 -0.0578 0.9584 0.0354
-5.750 -0.1359 0.07732 0.07264 -0.0625 0.9520 0.0369
-5.500 -0.1054 0.07371 0.06897 -0.0692 0.9470 0.0396
-5.250 -0.0450 0.07122 0.06627 -0.0875 0.9383 0.0431
-5.000 -0.0128 0.06660 0.06159 -0.0936 0.9344 0.0436
-4.750 -0.0044 0.06282 0.05786 -0.0914 0.9288 0.0447
-4.500 0.0184 0.05967 0.05467 -0.0937 0.9239 0.0466
-4.250 0.0842 0.05673 0.05140 -0.1086 0.9206 0.0542
-4.000 0.1050 0.05299 0.04766 -0.1104 0.9145 0.0553
-3.750 0.1263 0.05007 0.04474 -0.1113 0.9099 0.0576
-3.500 0.1934 0.04764 0.04186 -0.1237 0.9071 0.0657
-3.250 0.2055 0.04424 0.03861 -0.1226 0.9028 0.0681
-3.000 0.2468 0.04216 0.03628 -0.1280 0.8979 0.0786
-2.750 0.2720 0.03969 0.03382 -0.1293 0.8940 0.0828
-2.500 0.3175 0.03725 0.03113 -0.1348 0.8911 0.0925
-2.000 0.3815 0.03342 0.02705 -0.1391 0.8792 0.1094
-1.750 0.4240 0.03181 0.02515 -0.1429 0.8751 0.1328
-1.250 0.5074 0.02667 0.01899 -0.1471 0.8630 0.0651
-1.000 0.5397 0.02486 0.01710 -0.1484 0.8576 0.0610
-0.750 0.5746 0.02362 0.01527 -0.1489 0.8504 0.0546
-0.500 0.6082 0.02226 0.01372 -0.1498 0.8450 0.0537
-0.250 0.6364 0.02128 0.01253 -0.1498 0.8349 0.0555
0.000 0.6669 0.02032 0.01140 -0.1498 0.8257 0.0562
0.250 0.6963 0.01967 0.01051 -0.1495 0.8165 0.0549
0.500 0.7245 0.01915 0.00986 -0.1492 0.8088 0.0544
0.750 0.7529 0.01855 0.00919 -0.1490 0.8015 0.0542
1.000 0.7806 0.01809 0.00867 -0.1487 0.7940 0.0542
1.250 0.8084 0.01768 0.00824 -0.1484 0.7861 0.0544
1.500 0.8355 0.01728 0.00789 -0.1480 0.7777 0.0549
1.750 0.8634 0.01691 0.00750 -0.1476 0.7691 0.0563
2.000 0.8896 0.01675 0.00735 -0.1471 0.7584 0.0608
2.250 0.9168 0.01661 0.00718 -0.1466 0.7479 0.0647
2.500 0.9446 0.01646 0.00698 -0.1461 0.7372 0.0670
2.750 0.9706 0.01642 0.00698 -0.1455 0.7241 0.0712
3.000 0.9967 0.01640 0.00700 -0.1448 0.7098 0.0795
3.250 1.0183 0.01507 0.00718 -0.1435 0.6941 1.0000
3.500 1.0436 0.01517 0.00718 -0.1426 0.6747 1.0000
3.750 1.0673 0.01531 0.00727 -0.1414 0.6477 1.0000
4.000 1.0911 0.01545 0.00733 -0.1402 0.6109 1.0000
4.250 1.1148 0.01561 0.00724 -0.1389 0.5635 1.0000
4.500 1.1370 0.01601 0.00728 -0.1374 0.5179 1.0000
4.750 1.1585 0.01658 0.00757 -0.1360 0.4817 1.0000
5.000 1.1802 0.01719 0.00801 -0.1349 0.4537 1.0000
5.250 1.2025 0.01777 0.00847 -0.1338 0.4329 1.0000
5.500 1.2253 0.01832 0.00896 -0.1329 0.4169 1.0000
6.000 1.2696 0.01949 0.01005 -0.1310 0.3820 1.0000
6.250 1.2909 0.02008 0.01061 -0.1299 0.3633 1.0000
6.500 1.3120 0.02068 0.01120 -0.1288 0.3454 1.0000
6.750 1.3333 0.02126 0.01182 -0.1277 0.3299 1.0000
7.000 1.3545 0.02183 0.01249 -0.1267 0.3151 1.0000
7.250 1.3749 0.02241 0.01316 -0.1255 0.2978 1.0000
7.500 1.3941 0.02303 0.01384 -0.1241 0.2768 1.0000
7.750 1.4129 0.02364 0.01456 -0.1227 0.2483 1.0000
8.000 1.4292 0.02445 0.01536 -0.1210 0.2060 1.0000
8.250 1.4403 0.02576 0.01636 -0.1187 0.1622 1.0000
8.500 1.4507 0.02725 0.01766 -0.1163 0.1384 1.0000
8.750 1.4609 0.02871 0.01906 -0.1140 0.1223 1.0000
9.000 1.4709 0.03010 0.02047 -0.1117 0.1084 1.0000
9.250 1.4796 0.03143 0.02184 -0.1091 0.0968 1.0000
9.500 1.4883 0.03268 0.02319 -0.1066 0.0857 1.0000
9.750 1.4984 0.03386 0.02450 -0.1044 0.0750 1.0000
10.000 1.5067 0.03520 0.02593 -0.1021 0.0645 1.0000
10.250 1.5118 0.03682 0.02765 -0.0995 0.0553 1.0000
10.500 1.5129 0.03882 0.02967 -0.0967 0.0473 1.0000
10.750 1.5149 0.04083 0.03180 -0.0942 0.0400 1.0000
11.000 1.5153 0.04306 0.03414 -0.0917 0.0350 1.0000
11.250 1.5153 0.04538 0.03658 -0.0895 0.0317 1.0000
11.500 1.5123 0.04809 0.03940 -0.0873 0.0297 1.0000
11.750 1.5111 0.05075 0.04228 -0.0854 0.0279 1.0000
12.000 1.5097 0.05351 0.04521 -0.0837 0.0262 1.0000
12.250 1.5075 0.05642 0.04826 -0.0823 0.0247 1.0000
12.500 1.5025 0.05974 0.05168 -0.0811 0.0235 1.0000
12.750 1.4983 0.06312 0.05523 -0.0800 0.0225 1.0000
13.000 1.4948 0.06652 0.05885 -0.0790 0.0217 1.0000
13.250 1.4903 0.07014 0.06268 -0.0781 0.0210 1.0000
13.500 1.4852 0.07395 0.06670 -0.0775 0.0205 1.0000
13.750 1.4793 0.07795 0.07091 -0.0771 0.0200 1.0000
14.000 1.4727 0.08220 0.07536 -0.0771 0.0196 1.0000
14.250 1.4653 0.08670 0.08007 -0.0774 0.0192 1.0000
14.500 1.4568 0.09155 0.08516 -0.0781 0.0189 1.0000
14.750 1.4477 0.09670 0.09050 -0.0794 0.0186 1.0000
15.000 1.4379 0.10219 0.09618 -0.0811 0.0183 1.0000
15.250 1.4275 0.10800 0.10219 -0.0833 0.0180 1.0000
15.500 1.4164 0.11417 0.10855 -0.0860 0.0178 1.0000
15.750 1.4047 0.12074 0.11531 -0.0892 0.0176 1.0000
16.000 1.3923 0.12775 0.12252 -0.0930 0.0174 1.0000
16.250 1.3790 0.13536 0.13032 -0.0973 0.0174 1.0000
16.500 1.3641 0.14382 0.13900 -0.1026 0.0174 1.0000
16.750 1.3440 0.15437 0.14981 -0.1096 0.0177 1.0000
17.000 1.2901 0.17843 0.17424 -0.1259 0.0194 1.0000
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