GOE 222 (MVA H.33) AIRFOIL (goe222-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 222 (MVA H.33) AIRFOIL (goe222-il) Reynolds number: 50,000 Max Cl/Cd: 14.38 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe222-il-50000-n5.txt Download as CSV file: xf-goe222-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 222 (MVA H.33) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1628 0.12105 0.11386 -0.0899 0.9302 0.0801
-10.500 -0.1601 0.11641 0.10921 -0.0931 0.9266 0.0802
-10.250 -0.1660 0.11216 0.10497 -0.0948 0.9215 0.0805
-10.000 -0.1779 0.10801 0.10086 -0.0956 0.9150 0.0808
-9.750 -0.1870 0.10211 0.09497 -0.0989 0.9107 0.0810
-9.500 -0.2054 0.09648 0.08937 -0.1007 0.9048 0.0810
-9.250 -0.2302 0.09136 0.08429 -0.1011 0.8977 0.0808
-9.000 -0.2617 0.08396 0.07687 -0.1046 0.8926 0.0804
-8.750 -0.3066 0.07980 0.07274 -0.1025 0.8835 0.0798
-8.500 -0.3405 0.06946 0.06211 -0.1126 0.8769 0.0793
-8.250 -0.3579 0.06358 0.05590 -0.1179 0.8697 0.0794
-8.000 -0.3493 0.05887 0.05076 -0.1234 0.8650 0.0802
-7.750 -0.3259 0.05540 0.04686 -0.1281 0.8618 0.0817
-7.500 -0.3043 0.05420 0.04564 -0.1290 0.8585 0.0839
-7.250 -0.2935 0.05307 0.04441 -0.1287 0.8531 0.0859
-7.000 -0.2692 0.05146 0.04256 -0.1306 0.8492 0.0887
-6.750 -0.2381 0.04981 0.04058 -0.1332 0.8461 0.0915
-6.500 -0.2084 0.04874 0.03947 -0.1348 0.8431 0.0943
-6.250 -0.1952 0.04819 0.03890 -0.1340 0.8368 0.0972
-6.000 -0.1650 0.04718 0.03770 -0.1361 0.8325 0.1029
-5.750 -0.1285 0.04608 0.03659 -0.1391 0.8292 0.1101
-5.500 -0.1030 0.04533 0.03572 -0.1404 0.8236 0.1183
-5.250 -0.0720 0.04436 0.03484 -0.1430 0.8178 0.1313
-5.000 -0.0281 0.04307 0.03391 -0.1480 0.8139 0.1662
-4.750 -0.0021 0.04334 0.03454 -0.1482 0.8075 0.2124
-4.500 0.0230 0.04397 0.03512 -0.1477 0.8003 0.2505
-4.250 0.0598 0.04453 0.03548 -0.1487 0.7959 0.2842
-4.000 0.0737 0.04552 0.03638 -0.1466 0.7867 0.3032
-3.750 0.1053 0.04604 0.03670 -0.1470 0.7812 0.3259
-3.500 0.1327 0.04668 0.03720 -0.1467 0.7755 0.3463
-3.250 0.1438 0.04776 0.03838 -0.1430 0.7668 0.3566
-3.000 0.1770 0.04782 0.03830 -0.1434 0.7626 0.3716
-2.750 0.1999 0.04794 0.03820 -0.1440 0.7542 0.3835
-2.500 0.2246 0.04806 0.03828 -0.1432 0.7480 0.3910
-2.250 0.2659 0.04743 0.03740 -0.1459 0.7444 0.4030
-2.000 0.2777 0.04806 0.03801 -0.1440 0.7341 0.4085
-1.750 0.3168 0.04753 0.03719 -0.1469 0.7290 0.4193
-1.500 0.3521 0.04702 0.03662 -0.1476 0.7257 0.4252
-1.250 0.3632 0.04779 0.03732 -0.1462 0.7140 0.4304
-1.000 0.4029 0.04721 0.03652 -0.1487 0.7096 0.4389
-0.750 0.4226 0.04758 0.03686 -0.1480 0.7013 0.4434
-0.500 0.4485 0.04769 0.03687 -0.1483 0.6936 0.4491
-0.250 0.4892 0.04709 0.03605 -0.1508 0.6900 0.4571
0.000 0.4986 0.04813 0.03710 -0.1490 0.6781 0.4607
0.250 0.5316 0.04781 0.03671 -0.1498 0.6732 0.4667
0.500 0.5723 0.04714 0.03585 -0.1519 0.6704 0.4740
0.750 0.5771 0.04868 0.03740 -0.1500 0.6568 0.4779
1.000 0.6116 0.04825 0.03691 -0.1508 0.6535 0.4841
1.250 0.6176 0.04990 0.03855 -0.1493 0.6408 0.4889
1.500 0.6527 0.04957 0.03807 -0.1505 0.6370 0.4959
2.000 0.6891 0.05111 0.03956 -0.1493 0.6210 0.5067
2.250 0.7252 0.05064 0.03898 -0.1503 0.6184 0.5150
2.500 0.7229 0.05319 0.04159 -0.1483 0.6057 0.5189
2.750 0.7557 0.05292 0.04124 -0.1488 0.6028 0.5268
3.000 0.7561 0.05550 0.04382 -0.1474 0.5911 0.5322
3.250 0.7851 0.05539 0.04371 -0.1474 0.5878 0.5396
3.750 0.8108 0.05847 0.04680 -0.1461 0.5735 0.5542
4.000 0.8405 0.05845 0.04675 -0.1463 0.5709 0.5641
4.500 0.8604 0.06217 0.05055 -0.1446 0.5566 0.5801
4.750 0.8906 0.06200 0.05039 -0.1448 0.5542 0.5922
5.250 0.9025 0.06673 0.05527 -0.1429 0.5400 0.6116
5.500 0.9326 0.06650 0.05509 -0.1429 0.5376 0.6276
6.000 0.9435 0.07119 0.05999 -0.1409 0.5229 0.6556
6.250 0.9780 0.06998 0.05893 -0.1407 0.5205 0.6839
6.750 0.9910 0.07192 0.06144 -0.1364 0.5045 0.8369
7.250 1.0133 0.07482 0.06427 -0.1347 0.4882 1.0000
7.500 1.0504 0.07359 0.06294 -0.1347 0.4860 1.0000
8.000 1.0602 0.07866 0.06804 -0.1330 0.4695 1.0000
8.500 1.0698 0.08372 0.07315 -0.1313 0.4529 1.0000
8.750 1.1032 0.08265 0.07204 -0.1309 0.4505 1.0000
9.250 1.1123 0.08758 0.07707 -0.1291 0.4332 1.0000
9.750 1.1209 0.09264 0.08223 -0.1275 0.4159 1.0000
10.250 1.1304 0.09760 0.08730 -0.1261 0.3984 1.0000
10.500 1.1605 0.09657 0.08627 -0.1253 0.3958 1.0000
10.750 1.1398 0.10261 0.09241 -0.1249 0.3809 1.0000
11.000 1.1689 0.10165 0.09147 -0.1240 0.3786 1.0000
11.250 1.1449 0.10855 0.09847 -0.1242 0.3639 1.0000
11.750 1.1480 0.11496 0.10500 -0.1239 0.3475 1.0000
12.250 1.1481 0.12208 0.11224 -0.1242 0.3319 1.0000
12.500 1.1704 0.12211 0.11231 -0.1235 0.3294 1.0000
12.750 1.1444 0.13019 0.12047 -0.1253 0.3174 1.0000
13.000 1.1661 0.13027 0.12061 -0.1246 0.3148 1.0000
13.500 1.1577 0.13945 0.12992 -0.1266 0.3010 1.0000
13.750 1.1775 0.13986 0.13038 -0.1261 0.2986 1.0000
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Polar data table (+)
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