GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Reynolds number: 100,000 Max Cl/Cd: 54.36 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe165-il-100000.txt Download as CSV file: xf-goe165-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2979 0.10664 0.10212 -0.0305 1.0000 0.1075
-8.250 -0.3214 0.10582 0.10145 -0.0324 1.0000 0.1113
-8.000 -0.3522 0.10548 0.10130 -0.0327 1.0000 0.1120
-7.750 -0.3026 0.09911 0.09482 -0.0288 1.0000 0.1178
-7.500 -0.3093 0.09730 0.09311 -0.0279 1.0000 0.1229
-7.250 -0.3459 0.09722 0.09324 -0.0273 1.0000 0.1257
-7.000 -0.3299 0.09338 0.08942 -0.0243 1.0000 0.1296
-6.750 -0.3296 0.09167 0.08776 -0.0218 1.0000 0.1349
-6.250 -0.3478 0.08804 0.08436 -0.0190 1.0000 0.1448
-5.750 -0.3747 0.08534 0.08192 -0.0179 1.0000 0.1561
-5.500 -0.3667 0.08311 0.07974 -0.0216 0.9969 0.1690
-5.250 -0.2481 0.04046 0.03520 -0.0947 0.9936 0.0717
-5.000 -0.1933 0.03477 0.02887 -0.1030 0.9897 0.0659
-4.750 -0.1321 0.03123 0.02432 -0.1100 0.9852 0.0598
-4.500 -0.0805 0.02824 0.02093 -0.1147 0.9784 0.0579
-4.250 -0.0264 0.02608 0.01849 -0.1192 0.9728 0.0579
-4.000 0.0192 0.02459 0.01692 -0.1220 0.9634 0.0598
-3.750 0.0640 0.02327 0.01576 -0.1250 0.9548 0.0676
-3.500 0.1162 0.02208 0.01453 -0.1296 0.9477 0.0788
-3.250 0.1657 0.02090 0.01438 -0.1342 0.9375 0.3376
-3.000 0.1967 0.02303 0.01652 -0.1322 0.9234 0.3772
-2.750 0.2286 0.02419 0.01769 -0.1309 0.9113 0.4011
-2.500 0.2633 0.02496 0.01844 -0.1305 0.9022 0.4274
-2.250 0.3020 0.02452 0.01790 -0.1318 0.8941 0.4363
-2.000 0.3424 0.02386 0.01707 -0.1341 0.8847 0.4454
-1.750 0.3889 0.02314 0.01617 -0.1373 0.8777 0.4577
-1.500 0.4238 0.02277 0.01572 -0.1381 0.8657 0.4717
-1.250 0.4602 0.02231 0.01518 -0.1392 0.8536 0.4859
-1.000 0.4982 0.02176 0.01451 -0.1408 0.8408 0.4975
-0.750 0.5345 0.02112 0.01378 -0.1420 0.8267 0.5044
-0.500 0.5733 0.02064 0.01309 -0.1441 0.8107 0.5129
-0.250 0.6063 0.02013 0.01252 -0.1446 0.7934 0.5192
0.000 0.6431 0.01980 0.01195 -0.1461 0.7747 0.5273
0.250 0.6712 0.01953 0.01159 -0.1457 0.7529 0.5329
0.500 0.7034 0.01940 0.01123 -0.1462 0.7306 0.5400
0.750 0.7302 0.01931 0.01103 -0.1457 0.7052 0.5457
1.000 0.7573 0.01935 0.01088 -0.1452 0.6778 0.5525
1.250 0.7833 0.01941 0.01076 -0.1445 0.6482 0.5585
1.500 0.8080 0.01952 0.01072 -0.1436 0.6183 0.5647
1.750 0.8337 0.01969 0.01068 -0.1431 0.5904 0.5707
2.000 0.8583 0.01975 0.01061 -0.1423 0.5667 0.5759
2.250 0.8841 0.01990 0.01065 -0.1419 0.5460 0.5814
2.500 0.9107 0.02006 0.01072 -0.1417 0.5290 0.5861
2.750 0.9365 0.02017 0.01076 -0.1413 0.5141 0.5909
3.000 0.9626 0.02034 0.01083 -0.1410 0.4998 0.5959
3.250 0.9887 0.02054 0.01091 -0.1407 0.4862 0.6002
3.500 1.0143 0.02073 0.01105 -0.1403 0.4738 0.6047
3.750 1.0408 0.02102 0.01121 -0.1401 0.4626 0.6100
4.000 1.0674 0.02135 0.01153 -0.1400 0.4522 0.6148
4.250 1.0945 0.02171 0.01189 -0.1400 0.4443 0.6194
4.500 1.1217 0.02211 0.01227 -0.1400 0.4364 0.6247
4.750 1.1482 0.02252 0.01273 -0.1398 0.4287 0.6305
5.000 1.1751 0.02292 0.01310 -0.1397 0.4209 0.6369
5.250 1.2005 0.02337 0.01364 -0.1394 0.4133 0.6434
5.500 1.2272 0.02378 0.01410 -0.1393 0.4061 0.6501
5.750 1.2525 0.02426 0.01472 -0.1390 0.3997 0.6580
6.000 1.2777 0.02466 0.01527 -0.1386 0.3932 0.6677
6.250 1.3026 0.02510 0.01583 -0.1381 0.3861 0.6798
6.500 1.3258 0.02533 0.01615 -0.1373 0.3749 0.6962
6.750 1.3440 0.02536 0.01649 -0.1356 0.3624 0.7279
7.000 1.3620 0.02541 0.01687 -0.1337 0.3523 1.0000
7.250 1.3847 0.02578 0.01721 -0.1328 0.3420 1.0000
7.500 1.4028 0.02595 0.01738 -0.1312 0.3281 1.0000
7.750 1.4204 0.02615 0.01769 -0.1294 0.3156 1.0000
8.000 1.4384 0.02648 0.01822 -0.1277 0.3054 1.0000
8.250 1.4571 0.02683 0.01868 -0.1261 0.2959 1.0000
8.500 1.4732 0.02711 0.01905 -0.1241 0.2841 1.0000
8.750 1.4839 0.02730 0.01944 -0.1211 0.2632 1.0000
9.000 1.4970 0.02769 0.01994 -0.1187 0.2438 1.0000
9.250 1.5089 0.02825 0.02063 -0.1160 0.2137 1.0000
9.500 1.5012 0.02996 0.02179 -0.1110 0.1412 1.0000
9.750 1.4875 0.03284 0.02425 -0.1058 0.0725 1.0000
10.000 1.4698 0.03610 0.02723 -0.1008 0.0595 1.0000
10.250 1.4551 0.03923 0.03046 -0.0965 0.0538 1.0000
10.500 1.4464 0.04210 0.03357 -0.0935 0.0497 1.0000
10.750 1.4344 0.04550 0.03719 -0.0910 0.0470 1.0000
11.000 1.4197 0.04953 0.04144 -0.0894 0.0452 1.0000
11.250 1.4025 0.05430 0.04641 -0.0888 0.0441 1.0000
11.500 1.3840 0.05969 0.05198 -0.0890 0.0433 1.0000
11.750 1.3736 0.06437 0.05686 -0.0894 0.0420 1.0000
12.000 1.3622 0.06936 0.06204 -0.0901 0.0408 1.0000
12.250 1.3496 0.07462 0.06748 -0.0910 0.0398 1.0000
12.500 1.3374 0.07992 0.07292 -0.0920 0.0388 1.0000
12.750 1.3272 0.08494 0.07808 -0.0929 0.0377 1.0000
13.000 1.3204 0.08930 0.08252 -0.0933 0.0368 1.0000
13.250 1.3185 0.09259 0.08584 -0.0930 0.0357 1.0000
13.500 1.3245 0.09395 0.08713 -0.0910 0.0344 1.0000
13.750 1.3532 0.09101 0.08395 -0.0848 0.0330 1.0000
14.000 1.3782 0.09029 0.08324 -0.0807 0.0323 1.0000
14.250 1.4024 0.09043 0.08350 -0.0772 0.0318 1.0000
14.500 1.4142 0.09258 0.08581 -0.0756 0.0313 1.0000
14.750 1.4180 0.09578 0.08922 -0.0752 0.0308 1.0000
15.000 1.4181 0.09950 0.09316 -0.0753 0.0303 1.0000
15.250 1.4158 0.10361 0.09748 -0.0758 0.0300 1.0000
15.500 1.4109 0.10815 0.10225 -0.0768 0.0298 1.0000
15.750 1.4036 0.11318 0.10752 -0.0784 0.0298 1.0000
16.000 1.3941 0.11872 0.11331 -0.0805 0.0301 1.0000
16.250 1.3826 0.12474 0.11956 -0.0834 0.0304 1.0000
16.500 1.3695 0.13126 0.12632 -0.0869 0.0307 1.0000
16.750 1.3551 0.13826 0.13354 -0.0911 0.0310 1.0000
17.000 1.3399 0.14574 0.14122 -0.0960 0.0314 1.0000
17.250 1.3242 0.15368 0.14935 -0.1014 0.0317 1.0000
17.500 1.3081 0.16210 0.15794 -0.1074 0.0321 1.0000
17.750 1.2927 0.17080 0.16678 -0.1135 0.0325 1.0000
18.000 1.2794 0.17939 0.17548 -0.1194 0.0330 1.0000
18.250 1.2736 0.18642 0.18259 -0.1234 0.0336 1.0000
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