GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il) Reynolds number: 100,000 Max Cl/Cd: 48.95 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe223-il-100000-n5.txt Download as CSV file: xf-goe223-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 223 (MVA H.34) 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1842 0.09995 0.09493 -0.0965 0.9584 0.0425
-11.750 -0.2091 0.08855 0.08351 -0.1032 0.9515 0.0421
-11.500 -0.2550 0.07460 0.06939 -0.1143 0.9448 0.0411
-11.250 -0.2918 0.06563 0.06020 -0.1221 0.9338 0.0405
-11.000 -0.3157 0.05934 0.05366 -0.1279 0.9235 0.0403
-10.750 -0.3312 0.05449 0.04855 -0.1323 0.9132 0.0404
-10.500 -0.3466 0.05119 0.04503 -0.1342 0.9008 0.0405
-10.250 -0.3501 0.04781 0.04136 -0.1375 0.8912 0.0407
-10.000 -0.3447 0.04486 0.03807 -0.1395 0.8830 0.0411
-9.750 -0.3365 0.04246 0.03536 -0.1403 0.8746 0.0416
-9.500 -0.3225 0.04022 0.03277 -0.1414 0.8678 0.0427
-9.250 -0.3045 0.03819 0.03033 -0.1425 0.8626 0.0437
-9.000 -0.2884 0.03656 0.02855 -0.1421 0.8555 0.0445
-8.750 -0.2648 0.03494 0.02685 -0.1422 0.8508 0.0453
-8.500 -0.2405 0.03355 0.02536 -0.1423 0.8464 0.0460
-8.250 -0.2215 0.03254 0.02428 -0.1415 0.8390 0.0470
-8.000 -0.1963 0.03141 0.02305 -0.1416 0.8341 0.0486
-7.750 -0.1715 0.03041 0.02194 -0.1414 0.8291 0.0499
-7.500 -0.1509 0.02967 0.02112 -0.1404 0.8219 0.0508
-7.250 -0.1252 0.02886 0.02023 -0.1399 0.8170 0.0516
-7.000 -0.1023 0.02815 0.01957 -0.1391 0.8113 0.0525
-6.750 -0.0813 0.02755 0.01902 -0.1383 0.8038 0.0538
-6.500 -0.0539 0.02680 0.01824 -0.1387 0.7987 0.0559
-6.250 -0.0315 0.02625 0.01764 -0.1385 0.7906 0.0578
-6.000 -0.0045 0.02555 0.01681 -0.1390 0.7839 0.0594
-5.750 0.0240 0.02475 0.01590 -0.1401 0.7777 0.0611
-5.500 0.0496 0.02403 0.01511 -0.1409 0.7692 0.0635
-5.250 0.0815 0.02320 0.01414 -0.1424 0.7637 0.0670
-5.000 0.1069 0.02263 0.01353 -0.1429 0.7542 0.0728
-4.750 0.1385 0.02178 0.01263 -0.1444 0.7475 0.0880
-4.500 0.1659 0.02087 0.01178 -0.1456 0.7379 0.1258
-4.250 0.1971 0.01977 0.01154 -0.1477 0.7305 0.3215
-4.000 0.2238 0.01992 0.01159 -0.1475 0.7203 0.3550
-3.750 0.2546 0.01993 0.01139 -0.1478 0.7130 0.3747
-3.500 0.2803 0.02017 0.01156 -0.1473 0.7024 0.3905
-3.250 0.3094 0.02029 0.01156 -0.1472 0.6947 0.4031
-3.000 0.3359 0.02043 0.01158 -0.1470 0.6843 0.4145
-2.750 0.3638 0.02049 0.01153 -0.1468 0.6756 0.4224
-2.500 0.3914 0.02059 0.01152 -0.1466 0.6664 0.4328
-2.250 0.4186 0.02078 0.01160 -0.1464 0.6575 0.4452
-2.000 0.4453 0.02094 0.01174 -0.1459 0.6497 0.4538
-1.750 0.4734 0.02098 0.01164 -0.1461 0.6419 0.4615
-1.500 0.5022 0.02089 0.01140 -0.1465 0.6348 0.4655
-1.250 0.5304 0.02085 0.01127 -0.1466 0.6285 0.4684
-1.000 0.5575 0.02088 0.01122 -0.1467 0.6212 0.4718
-0.750 0.5872 0.02083 0.01102 -0.1471 0.6157 0.4761
-0.500 0.6150 0.02088 0.01094 -0.1475 0.6090 0.4810
-0.250 0.6426 0.02091 0.01091 -0.1476 0.6030 0.4843
0.000 0.6718 0.02091 0.01081 -0.1479 0.5983 0.4876
0.250 0.6978 0.02105 0.01093 -0.1478 0.5921 0.4917
0.500 0.7260 0.02112 0.01090 -0.1481 0.5866 0.4966
0.750 0.7550 0.02116 0.01081 -0.1485 0.5812 0.5010
1.000 0.7796 0.02131 0.01099 -0.1481 0.5742 0.5046
1.250 0.8073 0.02138 0.01097 -0.1482 0.5681 0.5088
1.500 0.8341 0.02152 0.01104 -0.1483 0.5620 0.5139
1.750 0.8600 0.02169 0.01119 -0.1482 0.5560 0.5186
2.000 0.8876 0.02181 0.01128 -0.1483 0.5512 0.5231
2.250 0.9145 0.02199 0.01144 -0.1483 0.5465 0.5284
2.500 0.9396 0.02223 0.01166 -0.1482 0.5410 0.5339
2.750 0.9658 0.02239 0.01184 -0.1481 0.5360 0.5383
3.250 1.0177 0.02285 0.01231 -0.1480 0.5270 0.5506
3.500 1.0421 0.02310 0.01263 -0.1477 0.5224 0.5561
3.750 1.0686 0.02332 0.01286 -0.1476 0.5182 0.5626
4.000 1.0969 0.02353 0.01300 -0.1479 0.5139 0.5700
4.250 1.1166 0.02387 0.01350 -0.1469 0.5081 0.5757
4.500 1.1401 0.02413 0.01378 -0.1464 0.5023 0.5837
4.750 1.1677 0.02431 0.01392 -0.1465 0.4975 0.5918
5.000 1.1867 0.02471 0.01447 -0.1454 0.4926 0.6004
5.250 1.2076 0.02506 0.01492 -0.1446 0.4875 0.6092
5.500 1.2314 0.02531 0.01519 -0.1442 0.4825 0.6193
5.750 1.2524 0.02563 0.01559 -0.1433 0.4773 0.6292
6.000 1.2683 0.02608 0.01618 -0.1418 0.4711 0.6408
6.250 1.2884 0.02637 0.01654 -0.1408 0.4656 0.6532
6.500 1.3074 0.02671 0.01696 -0.1396 0.4604 0.6666
6.750 1.3182 0.02724 0.01769 -0.1373 0.4549 0.6805
7.000 1.3342 0.02767 0.01823 -0.1358 0.4497 0.6966
7.250 1.3548 0.02793 0.01857 -0.1349 0.4454 0.7159
7.500 1.3623 0.02873 0.01962 -0.1324 0.4395 0.7378
7.750 1.3735 0.02928 0.02041 -0.1304 0.4339 0.7701
8.000 1.3818 0.02932 0.02071 -0.1273 0.4290 1.0000
8.250 1.3860 0.03059 0.02212 -0.1250 0.4215 1.0000
8.500 1.3973 0.03146 0.02302 -0.1234 0.4145 1.0000
8.750 1.4022 0.03281 0.02448 -0.1214 0.4066 1.0000
9.000 1.4099 0.03401 0.02575 -0.1197 0.3988 1.0000
9.250 1.4129 0.03564 0.02750 -0.1178 0.3905 1.0000
9.500 1.4192 0.03705 0.02895 -0.1161 0.3820 1.0000
9.750 1.4184 0.03916 0.03118 -0.1142 0.3721 1.0000
10.000 1.4212 0.04101 0.03308 -0.1126 0.3623 1.0000
10.250 1.4231 0.04299 0.03511 -0.1111 0.3517 1.0000
10.500 1.4212 0.04542 0.03760 -0.1095 0.3399 1.0000
10.750 1.4209 0.04776 0.03997 -0.1080 0.3282 1.0000
11.000 1.4212 0.05009 0.04231 -0.1067 0.3170 1.0000
11.250 1.4219 0.05244 0.04462 -0.1055 0.3062 1.0000
11.500 1.4203 0.05517 0.04736 -0.1043 0.2957 1.0000
11.750 1.4195 0.05784 0.05004 -0.1033 0.2860 1.0000
12.000 1.4192 0.06044 0.05257 -0.1023 0.2764 1.0000
12.250 1.4161 0.06356 0.05570 -0.1014 0.2665 1.0000
12.500 1.4148 0.06644 0.05853 -0.1006 0.2572 1.0000
12.750 1.4131 0.06949 0.06160 -0.1000 0.2486 1.0000
13.000 1.4136 0.07224 0.06432 -0.0994 0.2408 1.0000
13.250 1.4130 0.07533 0.06749 -0.0990 0.2334 1.0000
13.500 1.4155 0.07786 0.07001 -0.0985 0.2267 1.0000
13.750 1.4160 0.08091 0.07316 -0.0983 0.2203 1.0000
14.000 1.4152 0.08409 0.07640 -0.0981 0.2130 1.0000
14.250 1.4151 0.08713 0.07946 -0.0979 0.2056 1.0000
14.500 1.4125 0.09075 0.08322 -0.0980 0.1980 1.0000
14.750 1.4123 0.09389 0.08638 -0.0980 0.1908 1.0000
15.000 1.4102 0.09761 0.09031 -0.0984 0.1831 1.0000
15.250 1.4079 0.10124 0.09406 -0.0987 0.1742 1.0000
15.500 1.4045 0.10515 0.09811 -0.0992 0.1611 1.0000
15.750 1.3983 0.10936 0.10229 -0.0999 0.1438 1.0000
16.000 1.3889 0.11403 0.10682 -0.1007 0.1337 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 223 (MVA H.34) AIRFOIL (goe223-il)