GOE 550 AIRFOIL (goe550-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 550 AIRFOIL (goe550-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.47 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe550-il-1000000.txt Download as CSV file: xf-goe550-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 550 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8537 0.08357 0.08081 -0.0640 1.0000 0.0222
-16.000 -0.8686 0.07824 0.07543 -0.0668 1.0000 0.0225
-15.750 -0.8836 0.07310 0.07024 -0.0695 1.0000 0.0227
-15.500 -0.9008 0.06786 0.06494 -0.0722 1.0000 0.0231
-15.250 -0.9277 0.06190 0.05892 -0.0753 1.0000 0.0231
-15.000 -0.9669 0.05496 0.05191 -0.0789 1.0000 0.0230
-14.750 -1.0772 0.04324 0.04005 -0.0823 1.0000 0.0217
-14.500 -1.1488 0.02891 0.02529 -0.0923 1.0000 0.0209
-14.250 -1.1520 0.02613 0.02239 -0.0916 1.0000 0.0215
-14.000 -1.1325 0.02446 0.02064 -0.0929 0.9991 0.0223
-13.750 -1.1030 0.02328 0.01938 -0.0951 0.9975 0.0233
-13.500 -1.0722 0.02237 0.01837 -0.0971 0.9958 0.0241
-13.250 -1.0420 0.02117 0.01708 -0.0993 0.9943 0.0251
-13.000 -1.0130 0.02005 0.01590 -0.1011 0.9927 0.0262
-12.750 -0.9842 0.01931 0.01510 -0.1022 0.9903 0.0272
-12.500 -0.9533 0.01868 0.01441 -0.1035 0.9882 0.0282
-12.250 -0.9209 0.01817 0.01382 -0.1049 0.9865 0.0290
-12.000 -0.8899 0.01713 0.01273 -0.1067 0.9848 0.0306
-11.750 -0.8561 0.01657 0.01214 -0.1085 0.9837 0.0318
-11.500 -0.8215 0.01608 0.01160 -0.1103 0.9828 0.0330
-11.250 -0.7951 0.01566 0.01111 -0.1102 0.9788 0.0337
-11.000 -0.7654 0.01488 0.01028 -0.1113 0.9758 0.0352
-10.750 -0.7324 0.01433 0.00971 -0.1127 0.9738 0.0367
-10.500 -0.6980 0.01391 0.00925 -0.1143 0.9723 0.0381
-10.250 -0.6625 0.01351 0.00880 -0.1160 0.9711 0.0392
-10.000 -0.6315 0.01293 0.00816 -0.1169 0.9680 0.0407
-9.750 -0.6033 0.01240 0.00761 -0.1172 0.9626 0.0425
-9.500 -0.5683 0.01200 0.00718 -0.1188 0.9596 0.0443
-9.250 -0.5322 0.01167 0.00680 -0.1206 0.9571 0.0457
-9.000 -0.5050 0.01120 0.00628 -0.1206 0.9495 0.0479
-8.750 -0.4713 0.01076 0.00582 -0.1219 0.9440 0.0504
-8.500 -0.4393 0.01045 0.00547 -0.1228 0.9364 0.0525
-8.250 -0.4060 0.01009 0.00505 -0.1239 0.9277 0.0552
-8.000 -0.3760 0.00973 0.00466 -0.1244 0.9160 0.0587
-7.750 -0.3458 0.00950 0.00436 -0.1248 0.9037 0.0616
-7.500 -0.3175 0.00919 0.00402 -0.1249 0.8903 0.0672
-7.250 -0.2899 0.00900 0.00377 -0.1247 0.8767 0.0724
-7.000 -0.2633 0.00879 0.00354 -0.1244 0.8636 0.0801
-6.750 -0.2367 0.00861 0.00334 -0.1241 0.8519 0.0877
-6.500 -0.2095 0.00854 0.00320 -0.1238 0.8411 0.0931
-6.250 -0.1831 0.00836 0.00301 -0.1234 0.8304 0.1005
-6.000 -0.1560 0.00828 0.00287 -0.1230 0.8208 0.1050
-5.500 -0.1023 0.00803 0.00256 -0.1224 0.8035 0.1156
-5.000 -0.0482 0.00781 0.00229 -0.1217 0.7868 0.1270
-4.750 -0.0212 0.00774 0.00217 -0.1214 0.7790 0.1325
-4.500 0.0060 0.00760 0.00206 -0.1211 0.7715 0.1426
-4.250 0.0329 0.00751 0.00197 -0.1208 0.7634 0.1540
-4.000 0.0602 0.00743 0.00191 -0.1205 0.7551 0.1657
-3.750 0.0873 0.00741 0.00185 -0.1201 0.7455 0.1754
-3.500 0.1144 0.00736 0.00181 -0.1198 0.7352 0.1842
-3.250 0.1416 0.00738 0.00177 -0.1194 0.7253 0.1904
-3.000 0.1689 0.00734 0.00174 -0.1192 0.7159 0.1976
-2.750 0.1964 0.00736 0.00173 -0.1189 0.7076 0.2040
-2.500 0.2241 0.00737 0.00170 -0.1186 0.6989 0.2086
-2.250 0.2513 0.00734 0.00166 -0.1183 0.6906 0.2134
-2.000 0.2787 0.00734 0.00164 -0.1180 0.6813 0.2173
-1.750 0.3061 0.00736 0.00162 -0.1177 0.6723 0.2205
-1.500 0.3334 0.00740 0.00160 -0.1174 0.6629 0.2227
-1.250 0.3606 0.00736 0.00156 -0.1171 0.6539 0.2271
-1.000 0.3873 0.00738 0.00155 -0.1167 0.6437 0.2311
-0.750 0.4148 0.00739 0.00155 -0.1164 0.6334 0.2348
-0.500 0.4418 0.00744 0.00155 -0.1160 0.6234 0.2376
-0.250 0.4688 0.00748 0.00155 -0.1157 0.6130 0.2398
0.000 0.4958 0.00747 0.00154 -0.1153 0.6033 0.2445
0.250 0.5223 0.00751 0.00156 -0.1149 0.5930 0.2487
0.500 0.5494 0.00756 0.00159 -0.1146 0.5823 0.2526
0.750 0.5762 0.00762 0.00162 -0.1142 0.5724 0.2557
1.000 0.6026 0.00766 0.00164 -0.1137 0.5625 0.2611
1.250 0.6296 0.00769 0.00168 -0.1134 0.5534 0.2669
1.500 0.6559 0.00778 0.00173 -0.1129 0.5426 0.2715
1.750 0.6823 0.00783 0.00177 -0.1125 0.5316 0.2764
2.000 0.7088 0.00788 0.00182 -0.1121 0.5219 0.2822
2.500 0.7616 0.00801 0.00194 -0.1112 0.5029 0.2941
2.750 0.7875 0.00808 0.00201 -0.1107 0.4929 0.3020
3.000 0.8135 0.00816 0.00208 -0.1102 0.4815 0.3110
3.250 0.8394 0.00822 0.00216 -0.1097 0.4701 0.3230
3.500 0.8647 0.00829 0.00225 -0.1092 0.4577 0.3415
3.750 0.8894 0.00832 0.00238 -0.1085 0.4452 0.3880
4.000 0.9139 0.00830 0.00253 -0.1078 0.4323 0.4763
4.250 0.9381 0.00829 0.00266 -0.1071 0.4195 0.5424
4.500 0.9531 0.00775 0.00289 -0.1044 0.4081 0.8449
4.750 0.9994 0.00784 0.00310 -0.1084 0.3913 1.0000
5.000 1.0231 0.00805 0.00325 -0.1075 0.3781 1.0000
5.500 1.0710 0.00845 0.00356 -0.1058 0.3562 1.0000
5.750 1.0945 0.00867 0.00373 -0.1048 0.3453 1.0000
6.000 1.1171 0.00894 0.00393 -0.1038 0.3319 1.0000
6.250 1.1401 0.00917 0.00412 -0.1028 0.3199 1.0000
6.500 1.1635 0.00938 0.00430 -0.1019 0.3097 1.0000
6.750 1.1860 0.00964 0.00451 -0.1008 0.2995 1.0000
7.000 1.2084 0.00989 0.00471 -0.0998 0.2877 1.0000
7.250 1.2307 0.01013 0.00492 -0.0987 0.2751 1.0000
7.500 1.2522 0.01041 0.00515 -0.0974 0.2618 1.0000
7.750 1.2728 0.01072 0.00541 -0.0961 0.2471 1.0000
8.000 1.2911 0.01114 0.00571 -0.0943 0.2263 1.0000
8.250 1.3040 0.01172 0.00612 -0.0916 0.1952 1.0000
8.500 1.3080 0.01264 0.00676 -0.0874 0.1499 1.0000
8.750 1.3176 0.01332 0.00731 -0.0842 0.1276 1.0000
9.000 1.3322 0.01381 0.00775 -0.0819 0.1173 1.0000
9.250 1.3469 0.01429 0.00820 -0.0796 0.1087 1.0000
9.500 1.3620 0.01476 0.00865 -0.0775 0.1009 1.0000
9.750 1.3775 0.01521 0.00910 -0.0755 0.0936 1.0000
10.000 1.3908 0.01578 0.00962 -0.0732 0.0833 1.0000
10.250 1.4019 0.01647 0.01022 -0.0707 0.0697 1.0000
10.500 1.4112 0.01725 0.01093 -0.0680 0.0580 1.0000
10.750 1.4211 0.01804 0.01168 -0.0655 0.0499 1.0000
11.000 1.4313 0.01884 0.01247 -0.0631 0.0442 1.0000
11.250 1.4405 0.01972 0.01334 -0.0607 0.0391 1.0000
11.500 1.4511 0.02055 0.01418 -0.0587 0.0355 1.0000
11.750 1.4607 0.02149 0.01513 -0.0566 0.0323 1.0000
12.000 1.4698 0.02249 0.01614 -0.0546 0.0296 1.0000
12.250 1.4784 0.02358 0.01726 -0.0526 0.0273 1.0000
12.500 1.4873 0.02469 0.01839 -0.0509 0.0254 1.0000
12.750 1.4927 0.02610 0.01983 -0.0489 0.0236 1.0000
13.000 1.5027 0.02725 0.02103 -0.0475 0.0225 1.0000
13.250 1.5101 0.02862 0.02244 -0.0460 0.0213 1.0000
13.500 1.5146 0.03028 0.02413 -0.0445 0.0201 1.0000
13.750 1.5203 0.03191 0.02582 -0.0431 0.0193 1.0000
14.000 1.5272 0.03349 0.02747 -0.0420 0.0187 1.0000
14.250 1.5327 0.03523 0.02927 -0.0409 0.0180 1.0000
14.500 1.5362 0.03722 0.03130 -0.0399 0.0174 1.0000
14.750 1.5370 0.03955 0.03369 -0.0389 0.0168 1.0000
15.000 1.5357 0.04216 0.03638 -0.0380 0.0162 1.0000
15.250 1.5393 0.04436 0.03865 -0.0374 0.0159 1.0000
15.500 1.5418 0.04674 0.04112 -0.0369 0.0155 1.0000
15.750 1.5436 0.04927 0.04371 -0.0366 0.0152 1.0000
16.000 1.5435 0.05207 0.04659 -0.0363 0.0149 1.0000
16.250 1.5425 0.05505 0.04964 -0.0362 0.0146 1.0000
16.500 1.5408 0.05821 0.05288 -0.0362 0.0143 1.0000
16.750 1.5354 0.06192 0.05666 -0.0365 0.0140 1.0000
17.000 1.5262 0.06619 0.06102 -0.0369 0.0136 1.0000
17.250 1.5151 0.07087 0.06581 -0.0377 0.0134 1.0000
17.500 1.5141 0.07428 0.06930 -0.0382 0.0132 1.0000
17.750 1.5111 0.07801 0.07312 -0.0390 0.0131 1.0000
18.000 1.5081 0.08180 0.07700 -0.0398 0.0128 1.0000
18.250 1.5034 0.08592 0.08121 -0.0409 0.0126 1.0000
18.500 1.4980 0.09022 0.08560 -0.0421 0.0125 1.0000
18.750 1.4911 0.09483 0.09030 -0.0435 0.0124 1.0000
19.000 1.4862 0.09916 0.09472 -0.0449 0.0121 1.0000
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