GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Reynolds number: 500,000 Max Cl/Cd: 85.7 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe165-il-500000.txt Download as CSV file: xf-goe165-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 165 (MVA MK.11) 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3270 0.11140 0.10922 -0.0309 1.0000 0.0151
-9.750 -0.3264 0.10777 0.10561 -0.0316 1.0000 0.0151
-9.500 -0.3344 0.10277 0.10066 -0.0318 1.0000 0.0156
-9.250 -0.3325 0.10044 0.09835 -0.0314 1.0000 0.0159
-9.000 -0.3311 0.09809 0.09602 -0.0310 1.0000 0.0162
-8.750 -0.3306 0.09571 0.09368 -0.0305 1.0000 0.0166
-8.500 -0.3324 0.09313 0.09113 -0.0301 1.0000 0.0170
-8.250 -0.3365 0.09050 0.08854 -0.0294 1.0000 0.0174
-8.000 -0.3254 0.08585 0.08390 -0.0341 0.9980 0.0182
-7.750 -0.3120 0.07979 0.07785 -0.0413 0.9949 0.0193
-7.500 -0.3014 0.06999 0.06806 -0.0523 0.9885 0.0207
-7.250 -0.2762 0.05359 0.05143 -0.0815 0.9792 0.0209
-7.000 -0.2241 0.03625 0.03343 -0.1170 0.9731 0.0223
-6.750 -0.1956 0.03371 0.03085 -0.1203 0.9665 0.0234
-6.500 -0.1526 0.03144 0.02824 -0.1266 0.9624 0.0272
-6.250 -0.1180 0.02732 0.02385 -0.1322 0.9569 0.0311
-6.000 -0.0834 0.02600 0.02236 -0.1347 0.9496 0.0353
-5.500 -0.0082 0.01647 0.01171 -0.1393 0.9343 0.0187
-5.250 0.0266 0.01407 0.00904 -0.1404 0.9237 0.0167
-5.000 0.0704 0.01271 0.00757 -0.1437 0.9130 0.0171
-4.750 0.1289 0.01153 0.00625 -0.1503 0.8992 0.0179
-4.500 0.1832 0.01072 0.00524 -0.1561 0.8709 0.0196
-4.250 0.2209 0.01028 0.00448 -0.1581 0.8229 0.0206
-4.000 0.2491 0.01004 0.00387 -0.1580 0.7758 0.0214
-3.750 0.2761 0.00984 0.00337 -0.1576 0.7463 0.0239
-3.500 0.3033 0.00973 0.00312 -0.1573 0.7260 0.0290
-3.250 0.3309 0.00962 0.00292 -0.1572 0.7103 0.0500
-3.000 0.3589 0.00932 0.00264 -0.1573 0.6969 0.1016
-2.500 0.4150 0.00866 0.00225 -0.1577 0.6752 0.2527
-2.250 0.4426 0.00861 0.00231 -0.1576 0.6658 0.3076
-1.750 0.4974 0.00886 0.00248 -0.1570 0.6437 0.3475
-1.500 0.5247 0.00898 0.00252 -0.1567 0.6315 0.3561
-1.250 0.5519 0.00909 0.00256 -0.1563 0.6192 0.3618
-1.000 0.5791 0.00920 0.00257 -0.1560 0.6068 0.3675
-0.750 0.6059 0.00930 0.00262 -0.1556 0.5906 0.3721
-0.500 0.6321 0.00944 0.00267 -0.1551 0.5665 0.3772
-0.250 0.6574 0.00966 0.00268 -0.1544 0.5237 0.3828
0.000 0.6790 0.01016 0.00282 -0.1531 0.4464 0.3872
0.250 0.7034 0.01058 0.00303 -0.1523 0.4110 0.3918
0.750 0.7551 0.01112 0.00331 -0.1514 0.3756 0.3995
1.000 0.7815 0.01133 0.00350 -0.1510 0.3643 0.4043
1.250 0.8080 0.01155 0.00365 -0.1507 0.3555 0.4091
1.500 0.8346 0.01174 0.00377 -0.1504 0.3467 0.4123
1.750 0.8613 0.01184 0.00387 -0.1501 0.3389 0.4151
2.000 0.8875 0.01202 0.00401 -0.1497 0.3310 0.4180
2.250 0.9143 0.01216 0.00415 -0.1494 0.3245 0.4217
2.500 0.9409 0.01233 0.00429 -0.1491 0.3185 0.4254
2.750 0.9672 0.01246 0.00441 -0.1488 0.3131 0.4286
3.000 0.9939 0.01256 0.00454 -0.1485 0.3064 0.4314
3.250 1.0197 0.01275 0.00471 -0.1481 0.2996 0.4345
3.500 1.0465 0.01286 0.00484 -0.1479 0.2938 0.4379
3.750 1.0726 0.01304 0.00499 -0.1475 0.2873 0.4411
4.000 1.0989 0.01313 0.00512 -0.1472 0.2808 0.4441
4.250 1.1247 0.01328 0.00528 -0.1468 0.2722 0.4464
4.500 1.1501 0.01348 0.00541 -0.1463 0.2569 0.4485
4.750 1.1750 0.01371 0.00557 -0.1458 0.2376 0.4509
5.000 1.1987 0.01406 0.00579 -0.1452 0.2131 0.4532
5.250 1.2115 0.01552 0.00667 -0.1428 0.1205 0.4550
5.500 1.2331 0.01605 0.00712 -0.1418 0.1012 0.4573
5.750 1.2531 0.01674 0.00768 -0.1405 0.0635 0.4596
6.000 1.2748 0.01725 0.00816 -0.1395 0.0570 0.4622
6.250 1.2977 0.01761 0.00860 -0.1386 0.0512 0.4648
6.500 1.3190 0.01814 0.00918 -0.1375 0.0446 0.4675
6.750 1.3428 0.01839 0.00944 -0.1368 0.0394 0.4701
7.000 1.3633 0.01890 0.00989 -0.1356 0.0196 0.4727
7.250 1.3828 0.01952 0.01053 -0.1341 0.0158 0.4754
7.500 1.4034 0.02001 0.01112 -0.1328 0.0142 0.4785
7.750 1.4230 0.02056 0.01180 -0.1313 0.0136 0.4818
8.000 1.4411 0.02120 0.01256 -0.1296 0.0129 0.4852
8.250 1.4574 0.02192 0.01343 -0.1277 0.0123 0.4885
8.500 1.4706 0.02276 0.01440 -0.1252 0.0118 0.4919
8.750 1.4793 0.02371 0.01548 -0.1220 0.0114 0.4953
9.000 1.4847 0.02497 0.01686 -0.1184 0.0109 0.4984
9.250 1.4833 0.02662 0.01868 -0.1140 0.0104 0.5012
9.750 1.4832 0.02984 0.02219 -0.1065 0.0099 0.5079
10.000 1.4865 0.03134 0.02381 -0.1037 0.0098 0.5120
10.250 1.4879 0.03309 0.02570 -0.1009 0.0096 0.5159
10.500 1.4878 0.03510 0.02785 -0.0984 0.0095 0.5203
10.750 1.4863 0.03743 0.03030 -0.0963 0.0094 0.5250
11.000 1.4836 0.04008 0.03309 -0.0945 0.0093 0.5300
11.250 1.4806 0.04298 0.03614 -0.0932 0.0091 0.5359
11.500 1.4769 0.04619 0.03949 -0.0922 0.0091 0.5427
11.750 1.4729 0.04957 0.04302 -0.0916 0.0090 0.5512
12.000 1.4689 0.05306 0.04666 -0.0911 0.0090 0.5628
12.250 1.4651 0.05656 0.05033 -0.0906 0.0089 0.5844
12.500 1.4602 0.05937 0.05378 -0.0897 0.0089 1.0000
12.750 1.4568 0.06280 0.05730 -0.0890 0.0089 1.0000
13.000 1.4543 0.06608 0.06068 -0.0882 0.0090 1.0000
13.250 1.4530 0.06914 0.06382 -0.0872 0.0091 1.0000
13.500 1.4533 0.07202 0.06679 -0.0860 0.0092 1.0000
13.750 1.4545 0.07486 0.06971 -0.0850 0.0092 1.0000
14.000 1.4545 0.07801 0.07297 -0.0846 0.0091 1.0000
14.250 1.4542 0.08127 0.07635 -0.0842 0.0090 1.0000
14.500 1.4539 0.08456 0.07975 -0.0839 0.0090 1.0000
14.750 1.4567 0.08725 0.08256 -0.0821 0.0094 1.0000
15.000 1.2217 0.09242 0.08812 -0.0631 0.0104 1.0000
15.250 1.2126 0.09505 0.09086 -0.0628 0.0104 1.0000
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Polar data table (+)
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