GOE 63 AIRFOIL (goe63-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 63 AIRFOIL (goe63-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.44 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe63-il-1000000.txt Download as CSV file: xf-goe63-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 63 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2203 0.10242 0.10023 -0.0277 0.8205 0.0167
-8.500 -0.2114 0.09977 0.09751 -0.0290 0.8056 0.0172
-8.250 -0.2021 0.09695 0.09465 -0.0307 0.7930 0.0178
-8.000 -0.1933 0.09407 0.09172 -0.0332 0.7818 0.0181
-7.750 -0.1855 0.09132 0.08892 -0.0358 0.7707 0.0181
-7.500 -0.1762 0.08851 0.08609 -0.0391 0.7608 0.0181
-7.250 -0.1612 0.08530 0.08282 -0.0440 0.7512 0.0182
-7.000 -0.1464 0.08173 0.07923 -0.0472 0.7424 0.0182
-6.750 -0.1341 0.07873 0.07618 -0.0473 0.7340 0.0183
-6.500 -0.1183 0.07601 0.07344 -0.0493 0.7261 0.0184
-6.250 -0.1008 0.07340 0.07079 -0.0519 0.7179 0.0186
-6.000 -0.0813 0.07079 0.06815 -0.0550 0.7100 0.0188
-5.750 -0.0603 0.06815 0.06545 -0.0584 0.7016 0.0191
-5.500 -0.0374 0.06533 0.06260 -0.0622 0.6941 0.0195
-5.250 -0.0127 0.06241 0.05963 -0.0663 0.6871 0.0201
-5.000 0.0218 0.05892 0.05605 -0.0732 0.6809 0.0211
-4.750 0.0600 0.05528 0.05231 -0.0810 0.6749 0.0212
-4.500 0.0943 0.05186 0.04879 -0.0866 0.6687 0.0212
-4.250 0.1236 0.04812 0.04497 -0.0907 0.6634 0.0213
-4.000 0.1455 0.04576 0.04259 -0.0919 0.6583 0.0215
-3.750 0.1713 0.04363 0.04041 -0.0938 0.6528 0.0217
-3.500 0.2000 0.04152 0.03823 -0.0963 0.6473 0.0219
-3.250 0.2307 0.03938 0.03604 -0.0990 0.6420 0.0223
-3.000 0.2629 0.03718 0.03375 -0.1018 0.6363 0.0229
-2.750 0.3065 0.03440 0.03076 -0.1061 0.6311 0.0245
-2.500 0.3456 0.03169 0.02791 -0.1093 0.6273 0.0246
-2.250 0.3798 0.02943 0.02553 -0.1114 0.6228 0.0247
-2.000 0.4088 0.02686 0.02286 -0.1134 0.6181 0.0250
-1.750 0.4380 0.02551 0.02143 -0.1146 0.6134 0.0252
-1.500 0.4687 0.02414 0.02001 -0.1159 0.6095 0.0255
-1.250 0.5003 0.02277 0.01854 -0.1171 0.6050 0.0261
-1.000 0.5332 0.02129 0.01692 -0.1182 0.6003 0.0273
-0.750 0.5728 0.01846 0.01373 -0.1197 0.5957 0.0289
-0.500 0.6025 0.01759 0.01282 -0.1205 0.5907 0.0292
-0.250 0.6324 0.01681 0.01196 -0.1211 0.5855 0.0297
0.000 0.6630 0.01600 0.01102 -0.1217 0.5800 0.0306
0.250 0.6968 0.01515 0.00990 -0.1217 0.5746 0.0329
0.500 0.7278 0.01359 0.00823 -0.1228 0.5681 0.0337
0.750 0.7572 0.01311 0.00768 -0.1232 0.5613 0.0344
1.000 0.7872 0.01259 0.00707 -0.1235 0.5523 0.0357
1.500 0.8499 0.01046 0.00437 -0.1239 0.5318 0.0332
1.750 0.8791 0.01000 0.00387 -0.1240 0.5192 0.0323
2.000 0.9080 0.00977 0.00354 -0.1241 0.5034 0.0325
2.250 0.9362 0.00978 0.00342 -0.1241 0.4826 0.0329
2.500 0.9645 0.00961 0.00312 -0.1242 0.4552 0.0330
2.750 0.9923 0.00957 0.00294 -0.1243 0.4225 0.0339
3.000 1.0195 0.00978 0.00299 -0.1242 0.3900 0.0349
3.250 1.0468 0.00999 0.00308 -0.1242 0.3659 0.0360
3.500 1.0744 0.01015 0.00316 -0.1242 0.3492 0.0372
4.000 1.1298 0.01040 0.00333 -0.1242 0.3249 0.0422
4.250 1.1574 0.01054 0.00344 -0.1242 0.3161 0.0469
4.500 1.1854 0.01062 0.00359 -0.1242 0.3081 0.0992
4.750 1.2076 0.00947 0.00395 -0.1235 0.3006 1.0000
5.000 1.2351 0.00964 0.00409 -0.1234 0.2935 1.0000
5.250 1.2620 0.00988 0.00426 -0.1233 0.2859 1.0000
5.500 1.2895 0.01004 0.00440 -0.1233 0.2803 1.0000
5.750 1.3164 0.01026 0.00458 -0.1232 0.2732 1.0000
6.000 1.3433 0.01046 0.00476 -0.1231 0.2663 1.0000
6.250 1.3700 0.01068 0.00494 -0.1229 0.2584 1.0000
6.500 1.3964 0.01092 0.00514 -0.1228 0.2508 1.0000
6.750 1.4228 0.01115 0.00535 -0.1226 0.2428 1.0000
7.000 1.4487 0.01141 0.00557 -0.1224 0.2347 1.0000
7.250 1.4742 0.01172 0.00582 -0.1221 0.2241 1.0000
7.500 1.4995 0.01203 0.00608 -0.1218 0.2126 1.0000
7.750 1.5242 0.01237 0.00637 -0.1214 0.2017 1.0000
8.000 1.5483 0.01277 0.00670 -0.1210 0.1897 1.0000
8.250 1.5718 0.01320 0.00706 -0.1204 0.1777 1.0000
8.500 1.5956 0.01357 0.00740 -0.1199 0.1687 1.0000
8.750 1.6190 0.01397 0.00777 -0.1194 0.1609 1.0000
9.000 1.6420 0.01438 0.00815 -0.1188 0.1534 1.0000
9.250 1.6648 0.01478 0.00854 -0.1181 0.1465 1.0000
9.500 1.6866 0.01525 0.00897 -0.1173 0.1389 1.0000
9.750 1.7088 0.01566 0.00937 -0.1166 0.1333 1.0000
10.000 1.7300 0.01611 0.00980 -0.1157 0.1274 1.0000
10.250 1.7506 0.01659 0.01028 -0.1148 0.1217 1.0000
10.500 1.7713 0.01702 0.01072 -0.1138 0.1170 1.0000
10.750 1.7895 0.01760 0.01127 -0.1125 0.1109 1.0000
11.000 1.8088 0.01805 0.01174 -0.1113 0.1068 1.0000
11.250 1.8250 0.01865 0.01233 -0.1097 0.1010 1.0000
11.500 1.8409 0.01922 0.01291 -0.1080 0.0961 1.0000
11.750 1.8526 0.01991 0.01358 -0.1057 0.0900 1.0000
12.000 1.8620 0.02070 0.01437 -0.1030 0.0833 1.0000
12.250 1.8677 0.02180 0.01543 -0.1001 0.0734 1.0000
12.500 1.8650 0.02358 0.01708 -0.0964 0.0567 1.0000
12.750 1.8459 0.02685 0.02017 -0.0918 0.0304 1.0000
13.000 1.8382 0.02962 0.02292 -0.0891 0.0205 1.0000
13.250 1.8408 0.03169 0.02504 -0.0875 0.0181 1.0000
13.500 1.8442 0.03374 0.02716 -0.0861 0.0170 1.0000
13.750 1.8458 0.03604 0.02954 -0.0849 0.0161 1.0000
14.000 1.8484 0.03831 0.03189 -0.0838 0.0154 1.0000
14.250 1.8517 0.04053 0.03419 -0.0829 0.0150 1.0000
14.500 1.8533 0.04297 0.03673 -0.0820 0.0146 1.0000
14.750 1.8532 0.04567 0.03951 -0.0812 0.0142 1.0000
15.000 1.8508 0.04863 0.04257 -0.0805 0.0139 1.0000
15.250 1.8463 0.05192 0.04595 -0.0798 0.0135 1.0000
15.500 1.8397 0.05556 0.04970 -0.0794 0.0132 1.0000
15.750 1.8298 0.05970 0.05396 -0.0791 0.0129 1.0000
16.000 1.8226 0.06365 0.05802 -0.0790 0.0127 1.0000
16.250 1.8184 0.06731 0.06178 -0.0790 0.0125 1.0000
16.500 1.8120 0.07136 0.06594 -0.0793 0.0124 1.0000
16.750 1.8041 0.07567 0.07036 -0.0796 0.0122 1.0000
17.000 1.7945 0.08034 0.07514 -0.0802 0.0120 1.0000
17.250 1.7838 0.08530 0.08022 -0.0810 0.0118 1.0000
17.500 1.7713 0.09062 0.08565 -0.0821 0.0117 1.0000
17.750 1.7571 0.09629 0.09144 -0.0834 0.0116 1.0000
18.000 1.7418 0.10230 0.09758 -0.0849 0.0115 1.0000
18.250 1.7258 0.10853 0.10393 -0.0868 0.0114 1.0000
18.500 1.7082 0.11511 0.11065 -0.0889 0.0113 1.0000
18.750 1.6908 0.12175 0.11741 -0.0912 0.0113 1.0000
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