GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il) Reynolds number: 500,000 Max Cl/Cd: 80.63 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe223-il-500000-n5.txt Download as CSV file: xf-goe223-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.5152 0.08660 0.08371 -0.0860 0.9377 0.0156
-15.250 -0.5499 0.07695 0.07383 -0.0917 0.9297 0.0157
-15.000 -0.5656 0.07083 0.06755 -0.0956 0.9210 0.0159
-14.750 -0.5771 0.06575 0.06232 -0.0986 0.9114 0.0160
-14.500 -0.5854 0.06118 0.05760 -0.1015 0.9007 0.0162
-14.250 -0.5920 0.05710 0.05336 -0.1040 0.8902 0.0164
-14.000 -0.5977 0.05336 0.04945 -0.1063 0.8802 0.0166
-13.750 -0.6019 0.04984 0.04576 -0.1085 0.8703 0.0169
-13.500 -0.6053 0.04647 0.04219 -0.1105 0.8614 0.0173
-13.250 -0.6075 0.04321 0.03869 -0.1125 0.8523 0.0178
-13.000 -0.6061 0.04036 0.03563 -0.1143 0.8442 0.0181
-12.750 -0.5973 0.03838 0.03357 -0.1158 0.8364 0.0183
-12.500 -0.5865 0.03660 0.03170 -0.1174 0.8298 0.0185
-12.250 -0.5740 0.03487 0.02991 -0.1192 0.8234 0.0187
-12.000 -0.5608 0.03321 0.02816 -0.1210 0.8173 0.0189
-11.750 -0.5466 0.03160 0.02646 -0.1228 0.8118 0.0192
-11.500 -0.5330 0.03007 0.02485 -0.1246 0.8060 0.0194
-11.250 -0.5140 0.02855 0.02321 -0.1271 0.8007 0.0198
-11.000 -0.4926 0.02709 0.02162 -0.1297 0.7962 0.0203
-10.750 -0.4689 0.02571 0.02011 -0.1323 0.7915 0.0209
-10.500 -0.4444 0.02451 0.01873 -0.1346 0.7862 0.0215
-10.250 -0.4195 0.02360 0.01762 -0.1361 0.7811 0.0219
-10.000 -0.3963 0.02262 0.01663 -0.1368 0.7758 0.0223
-9.750 -0.3712 0.02185 0.01582 -0.1377 0.7702 0.0227
-9.500 -0.3455 0.02117 0.01509 -0.1386 0.7654 0.0231
-9.250 -0.3191 0.02055 0.01440 -0.1395 0.7613 0.0236
-9.000 -0.2923 0.01993 0.01372 -0.1403 0.7568 0.0241
-8.750 -0.2656 0.01933 0.01305 -0.1410 0.7519 0.0247
-8.500 -0.2388 0.01874 0.01237 -0.1416 0.7472 0.0252
-8.250 -0.2115 0.01819 0.01175 -0.1423 0.7425 0.0257
-8.000 -0.1835 0.01774 0.01122 -0.1429 0.7367 0.0261
-7.750 -0.1569 0.01708 0.01050 -0.1435 0.7307 0.0267
-7.500 -0.1298 0.01643 0.00983 -0.1442 0.7246 0.0272
-7.250 -0.1019 0.01590 0.00927 -0.1449 0.7174 0.0276
-7.000 -0.0739 0.01543 0.00874 -0.1455 0.7108 0.0281
-6.750 -0.0453 0.01498 0.00825 -0.1462 0.7029 0.0286
-6.500 -0.0169 0.01460 0.00780 -0.1468 0.6948 0.0292
-6.250 0.0118 0.01423 0.00737 -0.1475 0.6850 0.0299
-6.000 0.0404 0.01388 0.00694 -0.1480 0.6746 0.0303
-5.750 0.0688 0.01357 0.00653 -0.1486 0.6618 0.0307
-5.500 0.0971 0.01331 0.00617 -0.1490 0.6463 0.0311
-5.250 0.1252 0.01311 0.00585 -0.1494 0.6275 0.0314
-5.000 0.1527 0.01281 0.00540 -0.1498 0.6048 0.0320
-4.500 0.2074 0.01252 0.00483 -0.1503 0.5655 0.0336
-4.250 0.2353 0.01243 0.00462 -0.1506 0.5523 0.0344
-4.000 0.2634 0.01235 0.00445 -0.1508 0.5415 0.0351
-3.750 0.2912 0.01232 0.00431 -0.1510 0.5316 0.0358
-3.500 0.3197 0.01226 0.00417 -0.1513 0.5232 0.0366
-3.250 0.3478 0.01224 0.00407 -0.1516 0.5161 0.0374
-3.000 0.3766 0.01217 0.00394 -0.1519 0.5109 0.0391
-2.750 0.4053 0.01210 0.00383 -0.1522 0.5059 0.0416
-2.500 0.4339 0.01199 0.00372 -0.1526 0.5012 0.0521
-2.250 0.4628 0.01169 0.00356 -0.1533 0.4965 0.1227
-2.000 0.4929 0.01086 0.00330 -0.1548 0.4916 0.3096
-1.750 0.5214 0.01088 0.00335 -0.1550 0.4864 0.3318
-1.500 0.5494 0.01097 0.00340 -0.1552 0.4817 0.3455
-1.250 0.5778 0.01103 0.00345 -0.1554 0.4778 0.3576
-1.000 0.6064 0.01107 0.00350 -0.1556 0.4740 0.3670
-0.750 0.6348 0.01115 0.00355 -0.1558 0.4701 0.3754
-0.500 0.6627 0.01123 0.00362 -0.1559 0.4662 0.3820
-0.250 0.6904 0.01134 0.00370 -0.1560 0.4628 0.3883
0.000 0.7188 0.01141 0.00376 -0.1562 0.4598 0.3953
0.250 0.7470 0.01147 0.00385 -0.1564 0.4562 0.4026
0.500 0.7749 0.01157 0.00392 -0.1565 0.4524 0.4096
0.750 0.8021 0.01168 0.00401 -0.1565 0.4480 0.4141
1.000 0.8295 0.01177 0.00409 -0.1565 0.4425 0.4171
1.250 0.8568 0.01186 0.00417 -0.1566 0.4356 0.4199
1.500 0.8833 0.01199 0.00427 -0.1565 0.4299 0.4229
1.750 0.9105 0.01210 0.00436 -0.1565 0.4247 0.4262
2.250 0.9630 0.01236 0.00458 -0.1562 0.4116 0.4322
2.500 0.9893 0.01248 0.00471 -0.1561 0.4039 0.4352
2.750 1.0143 0.01267 0.00486 -0.1558 0.3947 0.4385
3.000 1.0385 0.01288 0.00503 -0.1554 0.3823 0.4419
3.250 1.0603 0.01321 0.00525 -0.1545 0.3631 0.4454
3.500 1.0696 0.01414 0.00585 -0.1517 0.3031 0.4484
3.750 1.0724 0.01525 0.00665 -0.1478 0.2471 0.4514
4.000 1.0892 0.01583 0.00716 -0.1462 0.2300 0.4550
4.250 1.1089 0.01628 0.00758 -0.1452 0.2213 0.4589
4.500 1.1294 0.01669 0.00797 -0.1443 0.2150 0.4627
4.750 1.1490 0.01714 0.00841 -0.1433 0.2093 0.4664
5.000 1.1699 0.01752 0.00881 -0.1425 0.2052 0.4707
5.250 1.1906 0.01791 0.00923 -0.1418 0.2016 0.4758
5.500 1.2102 0.01837 0.00969 -0.1408 0.1976 0.4809
5.750 1.2292 0.01886 0.01021 -0.1399 0.1938 0.4860
6.000 1.2483 0.01935 0.01073 -0.1389 0.1905 0.4918
6.250 1.2683 0.01980 0.01121 -0.1382 0.1874 0.4976
6.500 1.2863 0.02036 0.01180 -0.1372 0.1812 0.5032
6.750 1.3031 0.02102 0.01248 -0.1360 0.1759 0.5098
7.000 1.3179 0.02181 0.01325 -0.1347 0.1618 0.5163
7.250 1.3205 0.02342 0.01469 -0.1322 0.1260 0.5224
7.500 1.3298 0.02464 0.01590 -0.1304 0.1169 0.5302
7.750 1.3432 0.02562 0.01692 -0.1292 0.1141 0.5390
8.000 1.3557 0.02669 0.01805 -0.1279 0.1113 0.5493
8.250 1.3681 0.02778 0.01920 -0.1267 0.1089 0.5600
8.500 1.3809 0.02886 0.02035 -0.1256 0.1072 0.5717
8.750 1.3934 0.03000 0.02157 -0.1245 0.1055 0.5846
9.000 1.4066 0.03109 0.02275 -0.1235 0.1045 0.5983
9.250 1.4196 0.03221 0.02396 -0.1226 0.1036 0.6129
9.500 1.4315 0.03343 0.02528 -0.1216 0.1022 0.6278
9.750 1.4421 0.03478 0.02672 -0.1205 0.1009 0.6430
10.000 1.4521 0.03622 0.02825 -0.1195 0.0996 0.6586
10.250 1.4607 0.03781 0.02992 -0.1184 0.0982 0.6740
10.500 1.4677 0.03958 0.03177 -0.1173 0.0966 0.6895
10.750 1.4734 0.04151 0.03380 -0.1161 0.0947 0.7061
11.000 1.4800 0.04341 0.03581 -0.1152 0.0929 0.7268
11.250 1.4930 0.04468 0.03730 -0.1147 0.0917 0.7756
11.500 1.5000 0.04586 0.03877 -0.1131 0.0893 1.0000
11.750 1.5075 0.04778 0.04073 -0.1124 0.0856 1.0000
12.000 1.5124 0.05000 0.04297 -0.1116 0.0811 1.0000
12.250 1.4973 0.05439 0.04714 -0.1101 0.0462 1.0000
12.500 1.4740 0.05990 0.05262 -0.1086 0.0211 1.0000
12.750 1.4704 0.06332 0.05609 -0.1079 0.0166 1.0000
13.000 1.4713 0.06628 0.05910 -0.1074 0.0151 1.0000
13.250 1.4723 0.06926 0.06215 -0.1070 0.0140 1.0000
13.500 1.4747 0.07207 0.06504 -0.1067 0.0133 1.0000
13.750 1.4766 0.07497 0.06801 -0.1064 0.0128 1.0000
14.000 1.4779 0.07796 0.07108 -0.1061 0.0123 1.0000
14.250 1.4788 0.08100 0.07419 -0.1059 0.0119 1.0000
14.500 1.4784 0.08425 0.07752 -0.1058 0.0115 1.0000
14.750 1.4769 0.08763 0.08098 -0.1056 0.0110 1.0000
15.000 1.4768 0.09084 0.08427 -0.1056 0.0107 1.0000
15.250 1.4774 0.09397 0.08748 -0.1055 0.0104 1.0000
15.500 1.4776 0.09720 0.09078 -0.1056 0.0101 1.0000
15.750 1.4774 0.10048 0.09414 -0.1057 0.0098 1.0000
16.000 1.4766 0.10388 0.09762 -0.1059 0.0095 1.0000
16.250 1.4757 0.10728 0.10110 -0.1062 0.0093 1.0000
16.500 1.4736 0.11088 0.10478 -0.1065 0.0091 1.0000
16.750 1.4716 0.11449 0.10847 -0.1070 0.0089 1.0000
17.000 1.4679 0.11841 0.11246 -0.1076 0.0087 1.0000
17.250 1.4632 0.12251 0.11664 -0.1083 0.0085 1.0000
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Polar data table (+)
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