GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Reynolds number: 100,000 Max Cl/Cd: 61.72 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe118-il-100000-n5.txt Download as CSV file: xf-goe118-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 118 (MVA MK.7) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2715 0.11660 0.11206 -0.0426 1.0000 0.0305
-9.000 -0.2722 0.11462 0.11017 -0.0435 1.0000 0.0306
-8.750 -0.2743 0.11269 0.10834 -0.0437 1.0000 0.0307
-8.500 -0.2620 0.10697 0.10265 -0.0415 1.0000 0.0316
-8.250 -0.2613 0.10452 0.10027 -0.0400 1.0000 0.0325
-8.000 -0.2601 0.10226 0.09808 -0.0397 0.9977 0.0334
-7.750 -0.2416 0.09828 0.09406 -0.0445 0.9883 0.0351
-7.500 -0.2236 0.09448 0.09027 -0.0503 0.9766 0.0375
-7.250 -0.2048 0.09154 0.08736 -0.0619 0.9568 0.0394
-7.000 -0.1898 0.08656 0.08239 -0.0623 0.9476 0.0411
-6.750 -0.1704 0.08299 0.07878 -0.0646 0.9375 0.0453
-6.500 -0.1366 0.08002 0.07575 -0.0820 0.9189 0.0503
-6.250 -0.1283 0.07510 0.07085 -0.0783 0.9108 0.0526
-6.000 -0.1093 0.07176 0.06746 -0.0800 0.9008 0.0567
-5.750 -0.0616 0.06859 0.06403 -0.0999 0.8845 0.0643
-5.500 -0.0554 0.06370 0.05923 -0.0965 0.8750 0.0657
-5.250 -0.0387 0.06030 0.05577 -0.0969 0.8644 0.0674
-5.000 -0.0017 0.05202 0.04722 -0.1059 0.8548 0.0292
-4.750 0.0263 0.04767 0.04271 -0.1102 0.8461 0.0257
-4.250 0.1003 0.03566 0.02992 -0.1215 0.8281 0.0200
-4.000 0.1325 0.03106 0.02479 -0.1248 0.8201 0.0195
-3.750 0.1643 0.02716 0.02024 -0.1270 0.8116 0.0192
-3.500 0.1964 0.02429 0.01663 -0.1282 0.8045 0.0197
-3.250 0.2259 0.02209 0.01381 -0.1287 0.7956 0.0213
-3.000 0.2551 0.02023 0.01153 -0.1290 0.7886 0.0228
-2.750 0.2835 0.01899 0.00999 -0.1290 0.7801 0.0241
-2.500 0.3120 0.01802 0.00871 -0.1289 0.7727 0.0266
-2.250 0.3402 0.01720 0.00764 -0.1288 0.7649 0.0325
-2.000 0.3684 0.01652 0.00678 -0.1287 0.7575 0.0401
-1.750 0.3965 0.01640 0.00683 -0.1286 0.7499 0.1116
-1.500 0.4240 0.01666 0.00686 -0.1286 0.7422 0.1459
-1.250 0.4515 0.01662 0.00662 -0.1286 0.7351 0.1631
-1.000 0.4782 0.01644 0.00632 -0.1284 0.7273 0.1665
-0.750 0.5054 0.01629 0.00600 -0.1282 0.7205 0.1708
-0.500 0.5321 0.01621 0.00581 -0.1281 0.7127 0.1767
-0.250 0.5598 0.01610 0.00560 -0.1280 0.7060 0.1855
0.000 0.5869 0.01602 0.00551 -0.1281 0.6982 0.2017
0.250 0.6145 0.01580 0.00540 -0.1281 0.6915 0.2587
0.750 0.6653 0.01441 0.00535 -0.1271 0.6769 1.0000
1.000 0.6916 0.01459 0.00541 -0.1269 0.6684 1.0000
1.250 0.7189 0.01474 0.00539 -0.1268 0.6618 1.0000
1.500 0.7450 0.01493 0.00553 -0.1266 0.6533 1.0000
1.750 0.7720 0.01509 0.00561 -0.1265 0.6467 1.0000
2.000 0.7981 0.01530 0.00580 -0.1263 0.6388 1.0000
2.250 0.8250 0.01547 0.00592 -0.1262 0.6324 1.0000
2.500 0.8510 0.01569 0.00616 -0.1260 0.6246 1.0000
2.750 0.8778 0.01588 0.00637 -0.1259 0.6184 1.0000
3.000 0.9036 0.01612 0.00668 -0.1257 0.6107 1.0000
3.250 0.9303 0.01632 0.00690 -0.1256 0.6047 1.0000
3.500 0.9559 0.01659 0.00734 -0.1254 0.5968 1.0000
3.750 0.9826 0.01680 0.00761 -0.1252 0.5909 1.0000
4.000 1.0078 0.01710 0.00810 -0.1249 0.5827 1.0000
4.250 1.0320 0.01719 0.00828 -0.1241 0.5675 1.0000
4.500 1.0505 0.01702 0.00803 -0.1217 0.5226 1.0000
4.750 1.0643 0.01736 0.00803 -0.1188 0.4432 1.0000
5.000 1.0604 0.01974 0.00898 -0.1141 0.2317 1.0000
5.250 1.0541 0.02310 0.01122 -0.1097 0.0350 1.0000
5.500 1.0693 0.02428 0.01259 -0.1077 0.0268 1.0000
5.750 1.0810 0.02566 0.01425 -0.1053 0.0236 1.0000
6.000 1.0940 0.02684 0.01568 -0.1031 0.0219 1.0000
6.250 1.1033 0.02817 0.01725 -0.1006 0.0194 1.0000
6.500 1.1060 0.02972 0.01904 -0.0972 0.0176 1.0000
6.750 1.1048 0.03158 0.02107 -0.0937 0.0170 1.0000
7.000 1.1010 0.03375 0.02337 -0.0904 0.0165 1.0000
7.250 1.0977 0.03607 0.02576 -0.0873 0.0161 1.0000
7.500 1.1007 0.03832 0.02791 -0.0843 0.0158 1.0000
7.750 1.1180 0.03979 0.02942 -0.0823 0.0154 1.0000
8.000 1.1374 0.04108 0.03087 -0.0807 0.0144 1.0000
8.250 1.1645 0.04255 0.03247 -0.0795 0.0133 1.0000
8.500 1.2112 0.04483 0.03486 -0.0799 0.0132 1.0000
8.750 1.2584 0.04818 0.03855 -0.0814 0.0135 1.0000
9.000 1.2914 0.05190 0.04256 -0.0816 0.0140 1.0000
9.250 1.3155 0.05605 0.04699 -0.0811 0.0147 1.0000
9.500 1.3368 0.05880 0.05009 -0.0795 0.0172 1.0000
9.750 1.3454 0.06183 0.05368 -0.0759 0.0203 1.0000
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Polar data table (+)
Polar graphs
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