GOE 7K AIRFOIL (goe07k-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 7K AIRFOIL (goe07k-il) Reynolds number: 500,000 Max Cl/Cd: 116.48 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe07k-il-500000-n5.txt Download as CSV file: xf-goe07k-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 7K 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1277 0.08429 0.08167 -0.1249 0.9455 0.0069
-9.500 -0.1312 0.08072 0.07812 -0.1253 0.9399 0.0071
-9.250 -0.1315 0.07593 0.07335 -0.1280 0.9364 0.0072
-9.000 -0.1252 0.07197 0.06938 -0.1313 0.9341 0.0071
-8.750 -0.1177 0.06753 0.06494 -0.1361 0.9323 0.0069
-8.500 -0.1204 0.06302 0.06044 -0.1401 0.9274 0.0068
-8.250 -0.1276 0.05826 0.05566 -0.1433 0.9211 0.0067
-8.000 -0.1240 0.04948 0.04674 -0.1518 0.9175 0.0069
-7.750 -0.1266 0.04466 0.04178 -0.1523 0.9120 0.0066
-7.250 -0.2024 0.01967 0.01489 -0.1389 0.8963 0.0067
-7.000 -0.1899 0.01777 0.01259 -0.1363 0.8928 0.0069
-6.750 -0.1676 0.01634 0.01078 -0.1356 0.8907 0.0074
-6.500 -0.1416 0.01507 0.00925 -0.1358 0.8892 0.0077
-6.250 -0.1096 0.01464 0.00875 -0.1373 0.8880 0.0084
-6.000 -0.0871 0.01398 0.00795 -0.1365 0.8858 0.0089
-5.750 -0.0809 0.01356 0.00742 -0.1318 0.8810 0.0094
-5.500 -0.0593 0.01297 0.00668 -0.1307 0.8783 0.0098
-5.250 -0.0335 0.01235 0.00596 -0.1306 0.8761 0.0107
-5.000 -0.0028 0.01194 0.00549 -0.1315 0.8745 0.0119
-4.750 0.0296 0.01149 0.00493 -0.1329 0.8732 0.0135
-4.500 0.0377 0.01126 0.00467 -0.1286 0.8689 0.0146
-4.250 0.0544 0.01101 0.00436 -0.1263 0.8653 0.0158
-4.000 0.0784 0.01071 0.00401 -0.1256 0.8628 0.0186
-3.750 0.1064 0.01043 0.00372 -0.1259 0.8609 0.0229
-3.500 0.1385 0.01020 0.00347 -0.1271 0.8594 0.0304
-3.250 0.1637 0.01010 0.00336 -0.1268 0.8570 0.0375
-3.000 0.1724 0.01008 0.00335 -0.1225 0.8521 0.0420
-2.750 0.1964 0.01004 0.00325 -0.1218 0.8491 0.0470
-2.500 0.2234 0.00986 0.00305 -0.1219 0.8469 0.0510
-2.250 0.2548 0.00971 0.00286 -0.1230 0.8452 0.0560
-2.000 0.2819 0.00961 0.00272 -0.1230 0.8430 0.0591
-1.750 0.2910 0.00961 0.00270 -0.1189 0.8383 0.0603
-1.500 0.3123 0.00950 0.00257 -0.1176 0.8351 0.0636
-1.250 0.3389 0.00939 0.00244 -0.1175 0.8327 0.0661
-1.000 0.3699 0.00927 0.00230 -0.1185 0.8308 0.0694
-0.750 0.3938 0.00923 0.00224 -0.1178 0.8280 0.0722
-0.500 0.4060 0.00922 0.00228 -0.1144 0.8233 0.0842
-0.250 0.4237 0.00886 0.00230 -0.1125 0.8200 0.2176
0.000 0.4468 0.00847 0.00230 -0.1119 0.8176 0.3624
0.250 0.4645 0.00772 0.00234 -0.1101 0.8154 0.6325
0.500 0.4646 0.00737 0.00255 -0.1038 0.8104 0.7944
1.000 0.7617 0.00781 0.00337 -0.1609 0.8194 0.9948
1.250 0.8030 0.00779 0.00333 -0.1643 0.8162 0.9967
1.500 0.8332 0.00779 0.00335 -0.1651 0.8096 1.0000
1.750 0.8509 0.00779 0.00334 -0.1630 0.8032 1.0000
2.000 0.8595 0.00781 0.00334 -0.1587 0.7934 1.0000
2.500 0.8914 0.00788 0.00340 -0.1537 0.7783 1.0000
2.750 0.9104 0.00792 0.00342 -0.1518 0.7697 1.0000
3.000 0.9236 0.00798 0.00346 -0.1486 0.7577 1.0000
3.250 0.9365 0.00807 0.00355 -0.1454 0.7471 1.0000
3.500 0.9502 0.00817 0.00363 -0.1423 0.7334 1.0000
3.750 0.9656 0.00829 0.00374 -0.1397 0.7222 1.0000
4.000 0.9797 0.00842 0.00387 -0.1368 0.7091 1.0000
4.250 0.9895 0.00861 0.00402 -0.1328 0.6888 1.0000
4.500 0.9888 0.00895 0.00422 -0.1266 0.6502 1.0000
4.750 0.9647 0.00981 0.00466 -0.1153 0.5663 1.0000
5.000 0.9476 0.01086 0.00532 -0.1060 0.4981 1.0000
5.500 0.9332 0.01298 0.00675 -0.0926 0.3558 1.0000
5.750 0.9323 0.01403 0.00746 -0.0874 0.2827 1.0000
6.000 0.9303 0.01525 0.00827 -0.0823 0.2031 1.0000
6.250 0.9343 0.01628 0.00897 -0.0784 0.1363 1.0000
6.500 0.9406 0.01726 0.00967 -0.0749 0.0812 1.0000
6.750 0.9542 0.01788 0.01023 -0.0727 0.0632 1.0000
7.000 0.9680 0.01849 0.01079 -0.0706 0.0452 1.0000
7.250 0.9800 0.01924 0.01142 -0.0682 0.0241 1.0000
7.500 0.9937 0.01991 0.01209 -0.0661 0.0174 1.0000
7.750 1.0077 0.02057 0.01276 -0.0641 0.0143 1.0000
8.000 1.0231 0.02115 0.01341 -0.0623 0.0124 1.0000
8.250 1.0372 0.02183 0.01412 -0.0603 0.0111 1.0000
8.500 1.0508 0.02255 0.01490 -0.0584 0.0099 1.0000
8.750 1.0654 0.02321 0.01561 -0.0566 0.0090 1.0000
9.000 1.0778 0.02404 0.01647 -0.0545 0.0081 1.0000
9.250 1.0906 0.02486 0.01738 -0.0525 0.0077 1.0000
9.500 1.1033 0.02569 0.01828 -0.0505 0.0072 1.0000
9.750 1.1158 0.02654 0.01918 -0.0486 0.0066 1.0000
10.000 1.1261 0.02756 0.02027 -0.0464 0.0064 1.0000
10.250 1.1359 0.02865 0.02144 -0.0442 0.0060 1.0000
10.500 1.1474 0.02963 0.02251 -0.0422 0.0057 1.0000
10.750 1.1569 0.03079 0.02379 -0.0400 0.0054 1.0000
11.000 1.1700 0.03165 0.02471 -0.0385 0.0050 1.0000
11.250 1.1785 0.03294 0.02609 -0.0363 0.0048 1.0000
11.500 1.1887 0.03407 0.02728 -0.0345 0.0046 1.0000
11.750 1.1957 0.03554 0.02884 -0.0323 0.0045 1.0000
12.000 1.2049 0.03687 0.03032 -0.0303 0.0043 1.0000
12.250 1.2129 0.03836 0.03195 -0.0283 0.0043 1.0000
12.500 1.2207 0.03995 0.03369 -0.0263 0.0042 1.0000
12.750 1.2277 0.04168 0.03563 -0.0243 0.0040 1.0000
13.000 1.2343 0.04340 0.03753 -0.0224 0.0039 1.0000
13.250 1.2386 0.04543 0.03975 -0.0202 0.0037 1.0000
13.500 1.2429 0.04726 0.04174 -0.0184 0.0035 1.0000
13.750 1.2469 0.04903 0.04363 -0.0168 0.0034 1.0000
14.000 1.2484 0.05121 0.04597 -0.0150 0.0034 1.0000
14.250 1.2452 0.05404 0.04901 -0.0129 0.0033 1.0000
14.500 1.2483 0.05577 0.05077 -0.0119 0.0032 1.0000
14.750 1.2393 0.05944 0.05470 -0.0099 0.0032 1.0000
15.000 1.2346 0.06239 0.05778 -0.0087 0.0031 1.0000
15.250 1.2245 0.06633 0.06199 -0.0073 0.0031 1.0000
15.500 1.2075 0.07135 0.06731 -0.0062 0.0030 1.0000
15.750 1.1889 0.07683 0.07306 -0.0057 0.0030 1.0000
16.000 1.1719 0.08236 0.07881 -0.0060 0.0030 1.0000
16.250 1.1474 0.08953 0.08627 -0.0072 0.0029 1.0000
16.500 1.1290 0.09609 0.09299 -0.0092 0.0030 1.0000
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