GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Reynolds number: 200,000 Max Cl/Cd: 83.14 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe118-il-200000.txt Download as CSV file: xf-goe118-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2667 0.09880 0.09565 -0.0388 1.0000 0.0270
-8.000 -0.2696 0.09687 0.09381 -0.0378 1.0000 0.0277
-7.750 -0.2854 0.09639 0.09344 -0.0340 1.0000 0.0279
-7.500 -0.2712 0.09281 0.08989 -0.0384 0.9948 0.0291
-7.250 -0.2482 0.08832 0.08539 -0.0453 0.9862 0.0306
-7.000 -0.2205 0.08349 0.08055 -0.0544 0.9764 0.0326
-6.750 -0.1790 0.07836 0.07538 -0.0716 0.9644 0.0345
-6.500 -0.1401 0.07320 0.07015 -0.0836 0.9553 0.0349
-6.250 -0.1328 0.06782 0.06480 -0.0825 0.9452 0.0367
-6.000 -0.1114 0.06466 0.06160 -0.0847 0.9338 0.0392
-5.750 -0.0853 0.06079 0.05765 -0.0906 0.9207 0.0429
-5.500 -0.0451 0.05434 0.05100 -0.1045 0.9066 0.0477
-5.250 -0.0337 0.05263 0.04930 -0.1017 0.8948 0.0505
-5.000 0.0070 0.04733 0.04368 -0.1122 0.8827 0.0592
-4.750 0.0198 0.04562 0.04196 -0.1098 0.8720 0.0623
-4.500 0.0561 0.04128 0.03728 -0.1163 0.8616 0.0720
-4.250 0.0746 0.03940 0.03539 -0.1154 0.8506 0.0770
-4.000 0.1048 0.03610 0.03184 -0.1185 0.8407 0.0875
-3.750 0.1337 0.03319 0.02868 -0.1202 0.8320 0.0918
-3.500 0.1817 0.01934 0.01299 -0.1253 0.8253 0.0388
-3.250 0.2113 0.01792 0.01102 -0.1248 0.8169 0.0351
-3.000 0.2394 0.01605 0.00875 -0.1246 0.8083 0.0342
-2.750 0.2673 0.01485 0.00729 -0.1243 0.7993 0.0343
-2.500 0.2952 0.01391 0.00614 -0.1240 0.7916 0.0355
-2.250 0.3227 0.01313 0.00521 -0.1239 0.7826 0.0434
-2.000 0.3507 0.01270 0.00474 -0.1236 0.7743 0.0536
-1.750 0.3788 0.01274 0.00480 -0.1233 0.7666 0.1061
-1.500 0.4065 0.01320 0.00510 -0.1233 0.7576 0.1364
-1.250 0.4338 0.01322 0.00499 -0.1232 0.7500 0.1480
-1.000 0.4609 0.01328 0.00496 -0.1232 0.7414 0.1649
-0.750 0.4879 0.01310 0.00479 -0.1231 0.7332 0.1739
-0.500 0.5153 0.01298 0.00455 -0.1230 0.7256 0.1780
-0.250 0.5422 0.01279 0.00440 -0.1229 0.7166 0.1839
0.000 0.5696 0.01269 0.00425 -0.1228 0.7093 0.1937
0.250 0.5968 0.01253 0.00417 -0.1228 0.7011 0.2134
0.500 0.6207 0.01068 0.00419 -0.1221 0.6943 1.0000
0.750 0.6483 0.01081 0.00413 -0.1219 0.6867 1.0000
1.000 0.6755 0.01096 0.00417 -0.1219 0.6795 1.0000
1.250 0.7029 0.01110 0.00419 -0.1218 0.6724 1.0000
1.500 0.7301 0.01125 0.00428 -0.1218 0.6651 1.0000
1.750 0.7574 0.01139 0.00434 -0.1217 0.6583 1.0000
2.000 0.7844 0.01155 0.00447 -0.1217 0.6508 1.0000
2.250 0.8117 0.01169 0.00458 -0.1216 0.6442 1.0000
2.500 0.8384 0.01184 0.00474 -0.1215 0.6360 1.0000
2.750 0.8658 0.01199 0.00481 -0.1214 0.6292 1.0000
3.000 0.8921 0.01212 0.00500 -0.1212 0.6201 1.0000
3.250 0.9188 0.01226 0.00515 -0.1210 0.6118 1.0000
3.500 0.9437 0.01219 0.00510 -0.1203 0.5948 1.0000
3.750 0.9682 0.01213 0.00495 -0.1194 0.5749 1.0000
4.000 0.9911 0.01209 0.00487 -0.1183 0.5451 1.0000
4.250 1.0135 0.01219 0.00488 -0.1172 0.5088 1.0000
4.500 1.0311 0.01269 0.00501 -0.1152 0.4274 1.0000
4.750 1.0315 0.01520 0.00613 -0.1113 0.1979 1.0000
5.000 1.0367 0.01763 0.00780 -0.1082 0.0406 1.0000
5.250 1.0577 0.01833 0.00869 -0.1069 0.0358 1.0000
5.500 1.0768 0.01918 0.00975 -0.1054 0.0329 1.0000
5.750 1.0903 0.02045 0.01123 -0.1033 0.0289 1.0000
6.000 1.0994 0.02195 0.01290 -0.1005 0.0278 1.0000
6.250 1.1051 0.02360 0.01465 -0.0973 0.0273 1.0000
6.500 1.1101 0.02518 0.01629 -0.0938 0.0272 1.0000
6.750 1.1176 0.02663 0.01779 -0.0908 0.0274 1.0000
7.000 1.1301 0.02790 0.01916 -0.0884 0.0281 1.0000
7.250 1.1474 0.02909 0.02045 -0.0863 0.0299 1.0000
7.500 1.1694 0.03119 0.02251 -0.0852 0.0285 1.0000
9.500 1.3920 0.05553 0.04866 -0.0805 0.0358 1.0000
9.750 1.3927 0.05708 0.05061 -0.0768 0.0333 1.0000
10.000 1.3945 0.05998 0.05379 -0.0740 0.0313 1.0000
10.250 1.3947 0.06334 0.05735 -0.0715 0.0297 1.0000
10.500 1.4096 0.07094 0.06486 -0.0724 0.0274 1.0000
10.750 1.3889 0.08171 0.07595 -0.0701 0.0264 1.0000
11.000 1.3743 0.08387 0.07840 -0.0662 0.0264 1.0000
11.250 1.3550 0.08569 0.08045 -0.0619 0.0263 1.0000
11.500 1.3334 0.08764 0.08261 -0.0579 0.0262 1.0000
11.750 1.3123 0.09017 0.08533 -0.0551 0.0261 1.0000
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Polar data table (+)
Polar graphs
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