GOE 342 AIRFOIL (goe342-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 342 AIRFOIL (goe342-il) Reynolds number: 500,000 Max Cl/Cd: 109.52 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe342-il-500000.txt Download as CSV file: xf-goe342-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1856 0.08755 0.08548 -0.0433 0.9909 0.0161
-8.250 -0.1713 0.08327 0.08119 -0.0449 0.9885 0.0164
-7.750 -0.2616 0.09475 0.09260 -0.0387 0.9917 0.0160
-7.500 -0.2453 0.09046 0.08830 -0.0396 0.9895 0.0163
-7.250 -0.2232 0.08687 0.08470 -0.0440 0.9859 0.0168
-7.000 -0.1972 0.08307 0.08089 -0.0501 0.9829 0.0174
-6.750 -0.1737 0.07943 0.07725 -0.0556 0.9753 0.0181
-6.500 -0.1439 0.07548 0.07327 -0.0630 0.9692 0.0192
-6.250 -0.1046 0.07156 0.06930 -0.0757 0.9571 0.0196
-6.000 -0.0707 0.06749 0.06516 -0.0851 0.9446 0.0196
-5.750 -0.0587 0.06350 0.06115 -0.0851 0.9338 0.0199
-5.500 -0.0465 0.06080 0.05841 -0.0843 0.9234 0.0202
-5.250 -0.0259 0.05811 0.05566 -0.0866 0.9121 0.0206
-5.000 -0.0003 0.05520 0.05269 -0.0905 0.9006 0.0213
-4.750 0.0293 0.05209 0.04951 -0.0954 0.8907 0.0224
-4.500 0.0881 0.04813 0.04532 -0.1078 0.8822 0.0240
-4.250 0.1297 0.04451 0.04152 -0.1143 0.8733 0.0241
-4.000 0.1471 0.04063 0.03760 -0.1156 0.8658 0.0246
-3.750 0.1713 0.03839 0.03532 -0.1171 0.8576 0.0250
-3.500 0.2007 0.03614 0.03295 -0.1197 0.8512 0.0258
-3.250 0.2341 0.03372 0.03043 -0.1229 0.8441 0.0270
-3.000 0.2833 0.03132 0.02770 -0.1276 0.8386 0.0296
-2.750 0.3206 0.02888 0.02501 -0.1303 0.8326 0.0298
-2.500 0.3488 0.02518 0.02122 -0.1330 0.8263 0.0306
-2.250 0.3766 0.02370 0.01965 -0.1341 0.8208 0.0313
-2.000 0.4067 0.02223 0.01808 -0.1354 0.8145 0.0324
-1.750 0.4384 0.02072 0.01638 -0.1366 0.8089 0.0340
-1.500 0.4741 0.02021 0.01549 -0.1368 0.8020 0.0370
-1.250 0.5057 0.01721 0.01225 -0.1386 0.7943 0.0382
-1.000 0.5341 0.01616 0.01115 -0.1392 0.7864 0.0393
-0.750 0.5633 0.01532 0.01019 -0.1397 0.7801 0.0413
-0.500 0.5933 0.01556 0.01017 -0.1393 0.7746 0.0460
-0.250 0.6241 0.01348 0.00796 -0.1406 0.7689 0.0489
0.000 0.6527 0.01295 0.00734 -0.1408 0.7634 0.0522
0.250 0.6820 0.01234 0.00660 -0.1411 0.7576 0.0603
0.500 0.7102 0.01210 0.00632 -0.1412 0.7511 0.0674
0.750 0.7385 0.01160 0.00577 -0.1415 0.7444 0.0782
1.500 0.8260 0.00975 0.00346 -0.1406 0.7171 0.0486
1.750 0.8539 0.00972 0.00343 -0.1403 0.7070 0.0466
2.000 0.8817 0.00946 0.00316 -0.1402 0.6954 0.0459
2.250 0.9095 0.00921 0.00290 -0.1401 0.6806 0.0468
2.500 0.9368 0.00911 0.00278 -0.1398 0.6599 0.0461
2.750 0.9635 0.00902 0.00262 -0.1395 0.6235 0.0459
3.000 0.9858 0.00946 0.00262 -0.1384 0.5311 0.0462
3.250 1.0083 0.01004 0.00281 -0.1375 0.4593 0.0478
3.500 1.0325 0.01047 0.00301 -0.1369 0.4166 0.0510
4.000 1.0810 0.00987 0.00370 -0.1362 0.3727 0.8693
4.750 1.1563 0.01058 0.00426 -0.1345 0.3360 1.0000
5.000 1.1816 0.01088 0.00452 -0.1341 0.3275 1.0000
5.250 1.2077 0.01109 0.00475 -0.1338 0.3195 1.0000
5.500 1.2330 0.01136 0.00500 -0.1334 0.3102 1.0000
5.750 1.2582 0.01164 0.00527 -0.1330 0.2987 1.0000
6.000 1.2836 0.01188 0.00550 -0.1326 0.2855 1.0000
6.250 1.3083 0.01218 0.00576 -0.1321 0.2680 1.0000
6.500 1.3325 0.01254 0.00602 -0.1316 0.2396 1.0000
6.750 1.3513 0.01348 0.00656 -0.1303 0.1644 1.0000
7.000 1.3693 0.01454 0.00733 -0.1289 0.1225 1.0000
7.250 1.3904 0.01522 0.00794 -0.1279 0.1062 1.0000
7.500 1.4124 0.01576 0.00847 -0.1271 0.0942 1.0000
7.750 1.4343 0.01631 0.00898 -0.1262 0.0833 1.0000
8.000 1.4558 0.01686 0.00951 -0.1252 0.0724 1.0000
8.250 1.4766 0.01747 0.01007 -0.1242 0.0619 1.0000
8.500 1.4969 0.01809 0.01066 -0.1231 0.0518 1.0000
8.750 1.5158 0.01885 0.01137 -0.1218 0.0375 1.0000
9.000 1.5320 0.01985 0.01229 -0.1200 0.0264 1.0000
9.250 1.5485 0.02076 0.01325 -0.1183 0.0224 1.0000
9.500 1.5642 0.02167 0.01419 -0.1164 0.0200 1.0000
9.750 1.5757 0.02289 0.01549 -0.1139 0.0182 1.0000
10.000 1.5892 0.02379 0.01649 -0.1117 0.0173 1.0000
10.250 1.5989 0.02477 0.01757 -0.1089 0.0165 1.0000
10.500 1.6069 0.02587 0.01878 -0.1059 0.0157 1.0000
10.750 1.6128 0.02717 0.02017 -0.1029 0.0151 1.0000
11.000 1.6146 0.02884 0.02193 -0.0995 0.0145 1.0000
11.250 1.6100 0.03113 0.02437 -0.0956 0.0140 1.0000
11.500 1.6128 0.03294 0.02630 -0.0929 0.0136 1.0000
11.750 1.6199 0.03441 0.02789 -0.0908 0.0133 1.0000
12.000 1.6248 0.03613 0.02974 -0.0887 0.0128 1.0000
12.250 1.6283 0.03805 0.03179 -0.0867 0.0124 1.0000
12.500 1.6304 0.04018 0.03405 -0.0847 0.0121 1.0000
12.750 1.6315 0.04249 0.03647 -0.0828 0.0118 1.0000
13.000 1.6318 0.04493 0.03903 -0.0811 0.0115 1.0000
13.250 1.6309 0.04757 0.04179 -0.0795 0.0113 1.0000
13.500 1.6288 0.05043 0.04476 -0.0781 0.0110 1.0000
13.750 1.6247 0.05358 0.04803 -0.0767 0.0108 1.0000
14.000 1.6188 0.05704 0.05162 -0.0754 0.0107 1.0000
14.250 1.6102 0.06096 0.05569 -0.0741 0.0105 1.0000
14.500 1.5991 0.06533 0.06024 -0.0729 0.0103 1.0000
15.000 1.5776 0.07445 0.06976 -0.0721 0.0102 1.0000
15.250 1.5685 0.07906 0.07454 -0.0727 0.0101 1.0000
15.500 1.5585 0.08405 0.07973 -0.0737 0.0101 1.0000
15.750 1.5473 0.08949 0.08535 -0.0752 0.0100 1.0000
16.000 1.5348 0.09540 0.09144 -0.0772 0.0100 1.0000
16.250 1.5217 0.10170 0.09793 -0.0797 0.0099 1.0000
16.500 1.5077 0.10844 0.10486 -0.0827 0.0099 1.0000
16.750 1.4932 0.11556 0.11215 -0.0863 0.0099 1.0000
17.000 1.4777 0.12309 0.11986 -0.0903 0.0099 1.0000
17.250 1.4623 0.13088 0.12782 -0.0947 0.0098 1.0000
17.500 1.4461 0.13907 0.13619 -0.0996 0.0099 1.0000
17.750 1.4300 0.14759 0.14486 -0.1049 0.0099 1.0000
18.000 1.4131 0.15663 0.15405 -0.1108 0.0099 1.0000
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