GOE 798 AIRFOIL (goe798-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 798 AIRFOIL (goe798-il) Reynolds number: 100,000 Max Cl/Cd: 31.88 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe798-il-100000-n5.txt Download as CSV file: xf-goe798-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 798 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0091 0.10620 0.10002 -0.1187 0.8922 0.0723
-11.000 -0.0129 0.10134 0.09512 -0.1213 0.8853 0.0732
-10.750 -0.0216 0.09570 0.08945 -0.1241 0.8787 0.0738
-10.500 -0.0223 0.09196 0.08570 -0.1255 0.8703 0.0742
-10.250 -0.0142 0.08923 0.08293 -0.1266 0.8644 0.0749
-10.000 -0.0096 0.08666 0.08035 -0.1274 0.8563 0.0758
-9.750 -0.0101 0.08307 0.07674 -0.1289 0.8490 0.0771
-9.500 -0.0237 0.07719 0.07082 -0.1321 0.8429 0.0785
-9.250 -0.2579 0.04587 0.03854 -0.1445 0.8244 0.0808
-9.000 -0.2498 0.04514 0.03777 -0.1427 0.8163 0.0815
-8.750 -0.2363 0.04398 0.03652 -0.1419 0.8110 0.0826
-8.500 -0.2241 0.04222 0.03454 -0.1413 0.8072 0.0842
-8.250 -0.2272 0.04004 0.03202 -0.1387 0.8001 0.0862
-8.000 -0.2256 0.03745 0.02893 -0.1366 0.7943 0.0885
-7.750 -0.2009 0.03680 0.02824 -0.1366 0.7906 0.0899
-7.500 -0.1772 0.03566 0.02692 -0.1367 0.7876 0.0919
-7.250 -0.1691 0.03467 0.02570 -0.1342 0.7807 0.0942
-7.000 -0.1534 0.03340 0.02408 -0.1329 0.7761 0.0971
-6.750 -0.1275 0.03289 0.02356 -0.1329 0.7728 0.0991
-6.500 -0.1016 0.03200 0.02249 -0.1331 0.7700 0.1022
-6.250 -0.0835 0.03099 0.02109 -0.1319 0.7658 0.1058
-6.000 -0.0655 0.03075 0.02092 -0.1305 0.7603 0.1077
-5.750 -0.0419 0.03031 0.02041 -0.1300 0.7562 0.1108
-5.500 -0.0160 0.02954 0.01935 -0.1299 0.7531 0.1151
-5.250 0.0132 0.02892 0.01869 -0.1304 0.7506 0.1181
-5.000 0.0391 0.02856 0.01829 -0.1303 0.7476 0.1215
-4.750 0.0529 0.02848 0.01811 -0.1281 0.7420 0.1250
-4.500 0.0752 0.02811 0.01763 -0.1273 0.7377 0.1283
-4.250 0.1024 0.02777 0.01731 -0.1274 0.7345 0.1316
-4.000 0.1323 0.02737 0.01680 -0.1278 0.7319 0.1358
-3.750 0.1638 0.02693 0.01618 -0.1286 0.7298 0.1400
-3.500 0.1793 0.02701 0.01636 -0.1267 0.7250 0.1429
-3.250 0.1957 0.02711 0.01649 -0.1249 0.7199 0.1464
-3.000 0.2204 0.02697 0.01625 -0.1244 0.7162 0.1508
-2.750 0.2488 0.02668 0.01594 -0.1246 0.7134 0.1546
-2.500 0.2800 0.02638 0.01564 -0.1253 0.7111 0.1583
-2.250 0.3138 0.02602 0.01522 -0.1264 0.7091 0.1620
-2.000 0.3173 0.02656 0.01580 -0.1224 0.7024 0.1639
-1.750 0.3356 0.02669 0.01589 -0.1209 0.6978 0.1666
-1.500 0.3618 0.02651 0.01577 -0.1207 0.6944 0.1698
-1.250 0.3943 0.02617 0.01542 -0.1215 0.6916 0.1737
-1.000 0.4322 0.02568 0.01488 -0.1231 0.6890 0.1782
-0.750 0.4317 0.02633 0.01559 -0.1183 0.6809 0.1806
-0.500 0.4548 0.02617 0.01546 -0.1174 0.6752 0.1848
-0.250 0.4919 0.02557 0.01485 -0.1188 0.6711 0.1921
0.000 0.5349 0.02488 0.01410 -0.1211 0.6679 0.2027
0.250 0.5255 0.02570 0.01508 -0.1149 0.6581 0.2075
0.500 0.5520 0.02552 0.01493 -0.1146 0.6536 0.2212
0.750 0.5856 0.02515 0.01463 -0.1156 0.6506 0.2447
1.000 0.6234 0.02468 0.01427 -0.1173 0.6481 0.2863
1.250 0.6111 0.02571 0.01549 -0.1108 0.6393 0.3075
1.500 0.6327 0.02554 0.01560 -0.1099 0.6346 0.3764
1.750 0.6637 0.02472 0.01542 -0.1103 0.6313 0.5583
2.000 0.7374 0.02366 0.01523 -0.1175 0.6289 0.9550
2.250 0.7343 0.02476 0.01638 -0.1129 0.6201 1.0000
2.500 0.7483 0.02496 0.01648 -0.1104 0.6147 1.0000
2.750 0.7833 0.02473 0.01610 -0.1116 0.6112 1.0000
3.000 0.7777 0.02549 0.01685 -0.1060 0.6041 1.0000
3.250 0.7793 0.02619 0.01751 -0.1018 0.5966 1.0000
3.500 0.8127 0.02591 0.01711 -0.1026 0.5928 1.0000
3.750 0.8148 0.02671 0.01789 -0.0987 0.5851 1.0000
4.000 0.8218 0.02738 0.01853 -0.0957 0.5772 1.0000
4.250 0.8580 0.02691 0.01794 -0.0967 0.5733 1.0000
4.500 0.8449 0.02855 0.01963 -0.0912 0.5620 1.0000
4.750 0.8727 0.02840 0.01938 -0.0911 0.5565 1.0000
5.250 0.8939 0.02986 0.02079 -0.0867 0.5398 1.0000
5.500 0.9298 0.02929 0.02012 -0.0876 0.5356 1.0000
5.750 0.9209 0.03119 0.02207 -0.0834 0.5230 1.0000
6.000 0.9538 0.03073 0.02151 -0.0838 0.5181 1.0000
6.250 0.9525 0.03236 0.02316 -0.0808 0.5064 1.0000
6.500 0.9829 0.03203 0.02274 -0.0809 0.5007 1.0000
6.750 0.9886 0.03332 0.02402 -0.0787 0.4900 1.0000
7.000 1.0156 0.03320 0.02382 -0.0785 0.4833 1.0000
7.250 1.0280 0.03411 0.02471 -0.0770 0.4742 1.0000
7.500 1.0491 0.03444 0.02498 -0.0763 0.4669 1.0000
7.750 1.0758 0.03442 0.02487 -0.0761 0.4611 1.0000
8.000 1.0836 0.03575 0.02621 -0.0744 0.4523 1.0000
8.250 1.1112 0.03568 0.02605 -0.0743 0.4471 1.0000
8.500 1.1275 0.03646 0.02681 -0.0734 0.4407 1.0000
8.750 1.1408 0.03747 0.02782 -0.0722 0.4341 1.0000
9.000 1.1671 0.03753 0.02780 -0.0721 0.4294 1.0000
9.250 1.1858 0.03817 0.02842 -0.0713 0.4239 1.0000
9.500 1.1936 0.03958 0.02986 -0.0698 0.4170 1.0000
9.750 1.2173 0.03980 0.03001 -0.0695 0.4118 1.0000
10.000 1.2370 0.04037 0.03054 -0.0689 0.4067 1.0000
10.250 1.2416 0.04207 0.03232 -0.0672 0.4004 1.0000
10.500 1.2594 0.04276 0.03297 -0.0665 0.3952 1.0000
10.750 1.2911 0.04243 0.03253 -0.0668 0.3912 1.0000
11.000 1.2873 0.04481 0.03504 -0.0647 0.3851 1.0000
11.250 1.2966 0.04619 0.03645 -0.0635 0.3795 1.0000
11.500 1.3196 0.04646 0.03667 -0.0632 0.3751 1.0000
11.750 1.3367 0.04726 0.03746 -0.0626 0.3707 1.0000
12.000 1.3319 0.04987 0.04021 -0.0607 0.3649 1.0000
12.250 1.3429 0.05118 0.04156 -0.0598 0.3603 1.0000
12.500 1.3655 0.05150 0.04185 -0.0595 0.3566 1.0000
12.750 1.3849 0.05212 0.04246 -0.0591 0.3529 1.0000
13.000 1.3708 0.05573 0.04627 -0.0571 0.3475 1.0000
13.250 1.3753 0.05770 0.04833 -0.0560 0.3429 1.0000
13.500 1.3941 0.05831 0.04894 -0.0556 0.3391 1.0000
13.750 1.4270 0.05764 0.04818 -0.0558 0.3359 1.0000
14.000 1.3928 0.06337 0.05420 -0.0533 0.3297 1.0000
14.250 1.3880 0.06638 0.05732 -0.0522 0.3243 1.0000
14.500 1.4089 0.06669 0.05762 -0.0519 0.3203 1.0000
14.750 1.4411 0.06587 0.05673 -0.0519 0.3170 1.0000
15.000 1.3744 0.07571 0.06695 -0.0495 0.3084 1.0000
15.250 1.3843 0.07722 0.06850 -0.0490 0.3037 1.0000
15.500 1.4166 0.07613 0.06736 -0.0489 0.3004 1.0000
15.750 1.3322 0.08917 0.08076 -0.0477 0.2888 1.0000
16.000 1.3557 0.08896 0.08055 -0.0475 0.2849 1.0000
16.250 1.3942 0.08684 0.07838 -0.0473 0.2822 1.0000
16.500 1.3059 0.10145 0.09331 -0.0477 0.2680 1.0000
16.750 1.3415 0.09947 0.09129 -0.0473 0.2659 1.0000
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