GOE 797 AIRFOIL (goe797-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 797 AIRFOIL (goe797-il) Reynolds number: 500,000 Max Cl/Cd: 108.23 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe797-il-500000.txt Download as CSV file: xf-goe797-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 797 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8219 0.04332 0.03972 -0.1132 0.9946 0.0393
-13.500 -0.8187 0.03948 0.03570 -0.1182 0.9902 0.0396
-13.250 -0.8113 0.03691 0.03297 -0.1205 0.9852 0.0400
-13.000 -0.7949 0.03463 0.03051 -0.1228 0.9823 0.0405
-12.750 -0.7792 0.03258 0.02827 -0.1241 0.9785 0.0409
-12.500 -0.7626 0.03071 0.02621 -0.1249 0.9737 0.0414
-12.250 -0.7415 0.02896 0.02425 -0.1260 0.9703 0.0420
-12.000 -0.7206 0.02752 0.02259 -0.1265 0.9663 0.0424
-11.750 -0.7033 0.02646 0.02133 -0.1257 0.9596 0.0428
-11.500 -0.6845 0.02466 0.01940 -0.1256 0.9550 0.0434
-11.250 -0.6644 0.02378 0.01850 -0.1248 0.9491 0.0440
-11.000 -0.6429 0.02310 0.01779 -0.1241 0.9427 0.0447
-10.750 -0.6204 0.02242 0.01703 -0.1235 0.9376 0.0454
-10.500 -0.6002 0.02171 0.01623 -0.1225 0.9297 0.0460
-10.250 -0.5784 0.02097 0.01536 -0.1217 0.9233 0.0468
-10.000 -0.5561 0.02029 0.01454 -0.1209 0.9164 0.0475
-9.750 -0.5331 0.01970 0.01380 -0.1202 0.9089 0.0481
-9.500 -0.5112 0.01868 0.01268 -0.1195 0.9023 0.0489
-9.250 -0.4879 0.01802 0.01200 -0.1189 0.8935 0.0498
-9.000 -0.4629 0.01754 0.01147 -0.1184 0.8864 0.0508
-8.750 -0.4379 0.01710 0.01097 -0.1180 0.8768 0.0519
-8.500 -0.4122 0.01667 0.01041 -0.1176 0.8692 0.0531
-8.250 -0.3862 0.01629 0.00992 -0.1173 0.8593 0.0540
-8.000 -0.3617 0.01553 0.00910 -0.1169 0.8511 0.0554
-7.750 -0.3356 0.01511 0.00866 -0.1166 0.8409 0.0567
-7.500 -0.3090 0.01478 0.00825 -0.1164 0.8324 0.0582
-7.250 -0.2820 0.01446 0.00784 -0.1163 0.8228 0.0598
-7.000 -0.2553 0.01406 0.00734 -0.1161 0.8149 0.0615
-6.750 -0.2286 0.01367 0.00696 -0.1160 0.8064 0.0636
-6.250 -0.1731 0.01324 0.00637 -0.1159 0.7914 0.0678
-6.000 -0.1463 0.01284 0.00594 -0.1158 0.7844 0.0706
-5.750 -0.1183 0.01264 0.00572 -0.1159 0.7781 0.0734
-5.500 -0.0899 0.01250 0.00550 -0.1159 0.7718 0.0761
-5.250 -0.0624 0.01221 0.00522 -0.1159 0.7662 0.0801
-5.000 -0.0338 0.01210 0.00505 -0.1161 0.7608 0.0840
-4.750 -0.0058 0.01186 0.00483 -0.1161 0.7552 0.0884
-4.500 0.0228 0.01177 0.00470 -0.1163 0.7501 0.0933
-4.250 0.0514 0.01164 0.00455 -0.1164 0.7456 0.0988
-4.000 0.0802 0.01156 0.00448 -0.1166 0.7406 0.1046
-3.750 0.1086 0.01142 0.00435 -0.1167 0.7352 0.1108
-3.500 0.1375 0.01144 0.00430 -0.1168 0.7297 0.1169
-3.250 0.1660 0.01131 0.00420 -0.1170 0.7246 0.1230
-3.000 0.1948 0.01127 0.00416 -0.1171 0.7194 0.1290
-2.750 0.2236 0.01120 0.00405 -0.1173 0.7148 0.1346
-2.500 0.2524 0.01116 0.00398 -0.1175 0.7101 0.1407
-2.250 0.2812 0.01111 0.00394 -0.1177 0.7053 0.1460
-2.000 0.3096 0.01096 0.00381 -0.1178 0.7004 0.1521
-1.750 0.3383 0.01090 0.00373 -0.1179 0.6956 0.1582
-1.500 0.3673 0.01091 0.00369 -0.1181 0.6911 0.1635
-1.250 0.3954 0.01074 0.00359 -0.1182 0.6860 0.1711
-1.000 0.4240 0.01066 0.00352 -0.1184 0.6810 0.1784
-0.750 0.4527 0.01060 0.00345 -0.1185 0.6766 0.1875
-0.500 0.4814 0.01055 0.00342 -0.1187 0.6723 0.1983
-0.250 0.5097 0.01042 0.00339 -0.1189 0.6678 0.2151
0.000 0.5380 0.01027 0.00337 -0.1191 0.6633 0.2465
0.250 0.5661 0.01007 0.00336 -0.1192 0.6592 0.3133
0.500 0.5934 0.00973 0.00340 -0.1194 0.6551 0.4354
0.750 0.6182 0.00914 0.00348 -0.1191 0.6506 0.6347
1.000 0.6396 0.00868 0.00360 -0.1174 0.6461 0.8143
1.250 0.6615 0.00856 0.00369 -0.1155 0.6417 0.9169
1.500 0.6967 0.00862 0.00373 -0.1167 0.6370 0.9666
1.750 0.7406 0.00866 0.00378 -0.1202 0.6312 0.9902
2.000 0.7880 0.00874 0.00380 -0.1245 0.6252 0.9999
2.250 0.8125 0.00882 0.00380 -0.1238 0.6198 1.0000
2.500 0.8367 0.00885 0.00384 -0.1231 0.6138 1.0000
2.750 0.8611 0.00891 0.00386 -0.1224 0.6077 1.0000
3.000 0.8859 0.00900 0.00389 -0.1218 0.6016 1.0000
3.250 0.9109 0.00906 0.00395 -0.1212 0.5944 1.0000
3.500 0.9359 0.00916 0.00399 -0.1207 0.5873 1.0000
3.750 0.9613 0.00924 0.00407 -0.1202 0.5793 1.0000
4.000 0.9859 0.00936 0.00412 -0.1196 0.5701 1.0000
4.250 1.0106 0.00946 0.00421 -0.1190 0.5587 1.0000
4.500 1.0345 0.00960 0.00430 -0.1183 0.5459 1.0000
4.750 1.0577 0.00978 0.00441 -0.1174 0.5314 1.0000
5.000 1.0801 0.00998 0.00455 -0.1164 0.5146 1.0000
5.250 1.1015 0.01024 0.00473 -0.1152 0.4957 1.0000
5.500 1.1214 0.01055 0.00494 -0.1137 0.4745 1.0000
5.750 1.1393 0.01095 0.00521 -0.1119 0.4526 1.0000
6.000 1.1567 0.01137 0.00551 -0.1101 0.4330 1.0000
6.500 1.1923 0.01214 0.00614 -0.1066 0.4035 1.0000
6.750 1.2085 0.01252 0.00647 -0.1045 0.3926 1.0000
7.000 1.2230 0.01299 0.00686 -0.1022 0.3822 1.0000
7.250 1.2417 0.01334 0.00720 -0.1007 0.3735 1.0000
7.500 1.2583 0.01380 0.00762 -0.0988 0.3664 1.0000
7.750 1.2780 0.01415 0.00798 -0.0976 0.3602 1.0000
8.000 1.2963 0.01458 0.00839 -0.0961 0.3538 1.0000
8.250 1.3127 0.01510 0.00888 -0.0944 0.3480 1.0000
8.500 1.3337 0.01543 0.00926 -0.0935 0.3433 1.0000
8.750 1.3522 0.01588 0.00971 -0.0922 0.3381 1.0000
9.000 1.3685 0.01644 0.01025 -0.0906 0.3327 1.0000
9.250 1.3878 0.01687 0.01072 -0.0896 0.3281 1.0000
9.500 1.4067 0.01733 0.01121 -0.0885 0.3229 1.0000
9.750 1.4229 0.01792 0.01179 -0.0870 0.3175 1.0000
10.000 1.4395 0.01851 0.01240 -0.0856 0.3123 1.0000
10.250 1.4582 0.01900 0.01294 -0.0846 0.3065 1.0000
10.500 1.4730 0.01970 0.01364 -0.0831 0.3004 1.0000
10.750 1.4893 0.02034 0.01432 -0.0819 0.2944 1.0000
11.000 1.5055 0.02099 0.01501 -0.0807 0.2870 1.0000
11.250 1.5183 0.02187 0.01587 -0.0791 0.2793 1.0000
11.500 1.5337 0.02261 0.01666 -0.0779 0.2698 1.0000
11.750 1.5463 0.02356 0.01760 -0.0765 0.2593 1.0000
12.000 1.5562 0.02469 0.01871 -0.0748 0.2467 1.0000
12.250 1.5648 0.02598 0.01996 -0.0731 0.2315 1.0000
12.500 1.5704 0.02751 0.02143 -0.0713 0.2137 1.0000
12.750 1.5725 0.02935 0.02319 -0.0692 0.1966 1.0000
13.000 1.5742 0.03128 0.02506 -0.0672 0.1839 1.0000
13.250 1.5757 0.03332 0.02705 -0.0654 0.1742 1.0000
13.500 1.5816 0.03505 0.02880 -0.0640 0.1670 1.0000
13.750 1.5834 0.03716 0.03090 -0.0624 0.1607 1.0000
14.000 1.5922 0.03871 0.03249 -0.0614 0.1557 1.0000
14.250 1.5959 0.04075 0.03455 -0.0601 0.1504 1.0000
14.500 1.6003 0.04275 0.03657 -0.0590 0.1456 1.0000
14.750 1.6086 0.04443 0.03832 -0.0581 0.1412 1.0000
15.000 1.6120 0.04659 0.04050 -0.0571 0.1367 1.0000
15.250 1.6158 0.04873 0.04268 -0.0561 0.1323 1.0000
15.500 1.6232 0.05058 0.04459 -0.0555 0.1277 1.0000
15.750 1.6255 0.05296 0.04699 -0.0546 0.1232 1.0000
16.000 1.6290 0.05526 0.04933 -0.0539 0.1193 1.0000
16.250 1.6348 0.05733 0.05147 -0.0534 0.1153 1.0000
16.500 1.6360 0.05992 0.05409 -0.0527 0.1112 1.0000
16.750 1.6371 0.06258 0.05679 -0.0522 0.1076 1.0000
17.000 1.6412 0.06493 0.05921 -0.0518 0.1034 1.0000
17.250 1.6396 0.06799 0.06229 -0.0514 0.0993 1.0000
17.500 1.6399 0.07083 0.06520 -0.0511 0.0955 1.0000
17.750 1.6396 0.07377 0.06819 -0.0509 0.0911 1.0000
18.000 1.6345 0.07736 0.07181 -0.0507 0.0871 1.0000
18.250 1.6337 0.08047 0.07499 -0.0507 0.0828 1.0000
18.500 1.6268 0.08440 0.07894 -0.0507 0.0786 1.0000
18.750 1.6237 0.08785 0.08246 -0.0509 0.0742 1.0000
19.000 1.6142 0.09218 0.08683 -0.0512 0.0699 1.0000
19.250 1.6078 0.09619 0.09090 -0.0517 0.0652 1.0000
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Polar data table (+)
Polar graphs
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