GOE 7K AIRFOIL (goe07k-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 7K AIRFOIL (goe07k-il) Reynolds number: 500,000 Max Cl/Cd: 122.3 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe07k-il-500000.txt Download as CSV file: xf-goe07k-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2181 0.10260 0.10009 -0.0972 0.9648 0.0200
-10.000 -0.2079 0.09850 0.09598 -0.1009 0.9639 0.0208
-9.750 -0.2014 0.09308 0.09057 -0.1082 0.9627 0.0221
-9.500 -0.1209 0.07230 0.06992 -0.1138 0.9519 0.0229
-9.250 -0.1095 0.06913 0.06674 -0.1152 0.9513 0.0234
-9.000 -0.1175 0.06716 0.06480 -0.1127 0.9449 0.0237
-8.750 -0.1128 0.06355 0.06118 -0.1144 0.9430 0.0243
-8.500 -0.1094 0.05927 0.05690 -0.1172 0.9415 0.0246
-8.250 -0.1067 0.05464 0.05227 -0.1209 0.9402 0.0251
-8.000 -0.1068 0.04944 0.04708 -0.1265 0.9390 0.0263
-7.750 -0.2106 0.06079 0.05827 -0.1246 0.9303 0.0235
-7.500 -0.1984 0.05759 0.05501 -0.1266 0.9284 0.0241
-7.250 -0.1845 0.05331 0.05062 -0.1296 0.9269 0.0248
-7.000 -0.1910 0.05087 0.04810 -0.1262 0.9197 0.0254
-6.750 -0.1820 0.04677 0.04385 -0.1266 0.9164 0.0262
-6.500 -0.1907 0.03476 0.03110 -0.1247 0.9135 0.0233
-6.250 -0.1962 0.03317 0.02939 -0.1187 0.9060 0.0210
-6.000 -0.1905 0.02860 0.02438 -0.1153 0.9028 0.0211
-5.750 -0.1813 0.02336 0.01847 -0.1121 0.9011 0.0212
-5.500 -0.1606 0.02011 0.01467 -0.1108 0.9003 0.0217
-5.250 -0.1349 0.01766 0.01177 -0.1106 0.8997 0.0230
-5.000 -0.1343 0.01736 0.01139 -0.1049 0.8924 0.0237
-4.750 -0.1076 0.01727 0.01130 -0.1050 0.8904 0.0255
-4.500 -0.0784 0.01643 0.01031 -0.1053 0.8893 0.0272
-4.250 -0.0466 0.01587 0.00960 -0.1061 0.8884 0.0290
-4.000 -0.0168 0.01458 0.00822 -0.1068 0.8877 0.0315
-3.750 0.0175 0.01438 0.00800 -0.1084 0.8870 0.0346
-3.500 0.0528 0.01417 0.00772 -0.1102 0.8864 0.0376
-3.250 0.0852 0.01325 0.00677 -0.1114 0.8858 0.0418
-3.000 0.0860 0.01342 0.00693 -0.1056 0.8788 0.0441
-2.750 0.1135 0.01320 0.00668 -0.1056 0.8765 0.0479
-2.500 0.1422 0.01254 0.00598 -0.1059 0.8751 0.0525
-2.250 0.1745 0.01218 0.00562 -0.1071 0.8740 0.0577
-2.000 0.2086 0.01191 0.00531 -0.1087 0.8731 0.0618
-1.750 0.2414 0.01143 0.00482 -0.1100 0.8722 0.0673
-1.500 0.2782 0.01115 0.00453 -0.1122 0.8715 0.0727
-1.250 0.3024 0.01107 0.00442 -0.1115 0.8689 0.0759
-0.500 0.4198 0.00863 0.00466 -0.1211 0.8641 0.8987
0.000 0.6259 0.00910 0.00507 -0.1555 0.8729 0.9840
0.250 0.7012 0.00917 0.00513 -0.1665 0.8739 0.9935
0.500 0.7667 0.00906 0.00502 -0.1753 0.8743 0.9993
0.750 0.8093 0.00893 0.00488 -0.1790 0.8725 1.0000
1.000 0.8511 0.00882 0.00475 -0.1824 0.8706 1.0000
1.250 0.8425 0.00887 0.00481 -0.1744 0.8614 1.0000
1.500 0.8870 0.00863 0.00454 -0.1782 0.8576 1.0000
1.750 0.8873 0.00864 0.00457 -0.1721 0.8493 1.0000
2.000 0.9279 0.00838 0.00428 -0.1750 0.8430 1.0000
2.250 0.9265 0.00845 0.00437 -0.1685 0.8354 1.0000
2.500 0.9564 0.00834 0.00426 -0.1691 0.8300 1.0000
2.750 0.9600 0.00836 0.00431 -0.1637 0.8215 1.0000
3.000 0.9904 0.00826 0.00420 -0.1643 0.8148 1.0000
3.250 0.9846 0.00826 0.00422 -0.1566 0.8040 1.0000
3.500 0.9879 0.00824 0.00419 -0.1510 0.7927 1.0000
3.750 0.9962 0.00822 0.00416 -0.1465 0.7801 1.0000
4.000 1.0046 0.00824 0.00415 -0.1420 0.7648 1.0000
4.250 1.0139 0.00829 0.00414 -0.1377 0.7441 1.0000
4.500 1.0188 0.00842 0.00424 -0.1326 0.7232 1.0000
4.750 1.0236 0.00862 0.00436 -0.1274 0.6963 1.0000
5.000 1.0212 0.00895 0.00453 -0.1206 0.6539 1.0000
5.250 1.0061 0.00960 0.00486 -0.1113 0.5856 1.0000
5.500 0.9858 0.01061 0.00547 -0.1012 0.5134 1.0000
6.000 0.9623 0.01292 0.00699 -0.0858 0.3582 1.0000
6.250 0.9550 0.01422 0.00782 -0.0795 0.2650 1.0000
6.500 0.9541 0.01542 0.00863 -0.0746 0.1904 1.0000
6.750 0.9548 0.01664 0.00941 -0.0701 0.1091 1.0000
7.000 0.9629 0.01754 0.01012 -0.0669 0.0749 1.0000
7.250 0.9756 0.01822 0.01075 -0.0645 0.0582 1.0000
7.500 0.9884 0.01892 0.01140 -0.0622 0.0447 1.0000
7.750 1.0008 0.01966 0.01212 -0.0597 0.0361 1.0000
8.000 1.0148 0.02032 0.01278 -0.0576 0.0311 1.0000
8.250 1.0252 0.02122 0.01372 -0.0550 0.0277 1.0000
8.500 1.0401 0.02184 0.01440 -0.0531 0.0257 1.0000
8.750 1.0530 0.02261 0.01520 -0.0509 0.0237 1.0000
9.000 1.0617 0.02366 0.01629 -0.0482 0.0220 1.0000
9.250 1.0667 0.02507 0.01781 -0.0448 0.0209 1.0000
9.500 1.0817 0.02576 0.01857 -0.0431 0.0201 1.0000
9.750 1.0945 0.02663 0.01951 -0.0411 0.0190 1.0000
10.000 1.1090 0.02736 0.02027 -0.0395 0.0177 1.0000
10.250 1.1205 0.02840 0.02137 -0.0374 0.0171 1.0000
10.500 1.1312 0.02959 0.02260 -0.0353 0.0161 1.0000
10.750 1.1454 0.03145 0.02460 -0.0335 0.0153 1.0000
11.000 1.1622 0.03248 0.02573 -0.0321 0.0151 1.0000
11.250 1.1769 0.03346 0.02684 -0.0306 0.0144 1.0000
11.500 1.1936 0.03471 0.02822 -0.0292 0.0140 1.0000
11.750 1.2101 0.03609 0.02975 -0.0280 0.0137 1.0000
12.000 1.2199 0.03716 0.03090 -0.0260 0.0129 1.0000
12.250 1.2326 0.03872 0.03262 -0.0244 0.0126 1.0000
12.500 1.2397 0.03994 0.03391 -0.0224 0.0120 1.0000
12.750 1.2486 0.04172 0.03582 -0.0205 0.0117 1.0000
13.000 1.2556 0.04477 0.03908 -0.0186 0.0113 1.0000
13.250 1.2545 0.04829 0.04291 -0.0158 0.0112 1.0000
13.500 1.2493 0.05139 0.04626 -0.0128 0.0112 1.0000
13.750 1.2344 0.05557 0.05074 -0.0093 0.0112 1.0000
14.000 1.2193 0.05858 0.05400 -0.0061 0.0110 1.0000
14.250 1.2032 0.06222 0.05788 -0.0033 0.0110 1.0000
14.500 1.1821 0.06759 0.06348 -0.0009 0.0111 1.0000
14.750 1.1640 0.07175 0.06785 0.0008 0.0111 1.0000
15.000 1.1569 0.07463 0.07085 0.0018 0.0112 1.0000
15.250 1.1257 0.08054 0.07705 0.0023 0.0109 1.0000
15.500 1.1144 0.08517 0.08177 0.0024 0.0112 1.0000
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