GOE 433 AIRFOIL (goe433-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 433 AIRFOIL (goe433-il) Reynolds number: 50,000 Max Cl/Cd: 22.75 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe433-il-50000-n5.txt Download as CSV file: xf-goe433-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 433 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2857 0.11571 0.10791 -0.0461 1.0000 0.1287
-10.250 -0.2984 0.11385 0.10614 -0.0445 1.0000 0.1292
-10.000 -0.3132 0.11203 0.10441 -0.0427 1.0000 0.1294
-9.750 -0.3061 0.10730 0.09965 -0.0473 0.9931 0.1303
-9.500 -0.3032 0.10175 0.09406 -0.0531 0.9845 0.1322
-9.250 -0.3103 0.09459 0.08685 -0.0605 0.9751 0.1339
-9.000 -0.2938 0.09085 0.08310 -0.0644 0.9670 0.1354
-8.750 -0.2718 0.08831 0.08052 -0.0672 0.9587 0.1375
-8.500 -0.2558 0.08456 0.07675 -0.0716 0.9504 0.1403
-8.250 -0.2581 0.07931 0.07146 -0.0765 0.9380 0.1429
-8.000 -0.3445 0.05682 0.04850 -0.1021 0.9141 0.1473
-7.750 -0.3365 0.05349 0.04504 -0.1050 0.9014 0.1501
-7.500 -0.3088 0.05198 0.04347 -0.1071 0.8942 0.1534
-7.250 -0.2972 0.04816 0.03935 -0.1110 0.8827 0.1573
-7.000 -0.2811 0.04300 0.03344 -0.1175 0.8730 0.1632
-6.750 -0.2540 0.04244 0.03299 -0.1176 0.8647 0.1665
-6.500 -0.2204 0.04108 0.03152 -0.1198 0.8594 0.1715
-6.250 -0.2018 0.03929 0.02939 -0.1210 0.8486 0.1768
-6.000 -0.1701 0.03800 0.02797 -0.1228 0.8425 0.1823
-5.750 -0.1446 0.03741 0.02735 -0.1230 0.8344 0.1877
-5.500 -0.1167 0.03603 0.02563 -0.1246 0.8263 0.1951
-5.250 -0.0834 0.03541 0.02506 -0.1256 0.8213 0.2013
-5.000 -0.0620 0.03496 0.02451 -0.1254 0.8116 0.2085
-4.750 -0.0316 0.03421 0.02364 -0.1263 0.8049 0.2165
-4.500 0.0033 0.03356 0.02292 -0.1276 0.8003 0.2261
-4.250 0.0218 0.03337 0.02266 -0.1268 0.7895 0.2340
-4.000 0.0535 0.03291 0.02215 -0.1275 0.7836 0.2443
-3.750 0.0795 0.03264 0.02185 -0.1275 0.7759 0.2543
-3.500 0.1055 0.03238 0.02150 -0.1276 0.7676 0.2663
-3.250 0.1381 0.03199 0.02115 -0.1281 0.7625 0.2785
-3.000 0.1592 0.03199 0.02111 -0.1276 0.7530 0.2910
-2.750 0.1881 0.03173 0.02082 -0.1278 0.7464 0.3051
-2.500 0.2214 0.03133 0.02046 -0.1282 0.7420 0.3198
-2.250 0.2387 0.03160 0.02075 -0.1272 0.7314 0.3326
-2.000 0.2704 0.03130 0.02042 -0.1275 0.7259 0.3497
-1.750 0.2939 0.03148 0.02067 -0.1269 0.7183 0.3645
-1.500 0.3186 0.03160 0.02085 -0.1263 0.7106 0.3801
-1.250 0.3512 0.03139 0.02064 -0.1264 0.7058 0.3985
-1.000 0.3702 0.03188 0.02117 -0.1254 0.6965 0.4145
-0.750 0.3990 0.03190 0.02118 -0.1252 0.6903 0.4334
-0.500 0.4330 0.03167 0.02090 -0.1254 0.6861 0.4534
-0.250 0.4494 0.03236 0.02162 -0.1243 0.6756 0.4700
0.250 0.5075 0.03241 0.02161 -0.1239 0.6641 0.5091
0.500 0.5277 0.03293 0.02215 -0.1229 0.6553 0.5277
0.750 0.5587 0.03278 0.02199 -0.1227 0.6503 0.5487
1.000 0.5809 0.03318 0.02242 -0.1219 0.6429 0.5678
1.250 0.6031 0.03357 0.02283 -0.1211 0.6350 0.5861
1.500 0.6351 0.03335 0.02258 -0.1211 0.6303 0.6051
1.750 0.6536 0.03393 0.02322 -0.1199 0.6223 0.6198
2.000 0.6752 0.03435 0.02369 -0.1190 0.6146 0.6354
2.250 0.7069 0.03414 0.02347 -0.1189 0.6101 0.6531
2.500 0.7237 0.03494 0.02433 -0.1178 0.6017 0.6684
2.750 0.7439 0.03551 0.02495 -0.1169 0.5941 0.6852
3.000 0.7749 0.03534 0.02479 -0.1167 0.5896 0.7039
3.250 0.7867 0.03642 0.02598 -0.1150 0.5811 0.7200
3.500 0.8039 0.03711 0.02677 -0.1137 0.5735 0.7389
3.750 0.8342 0.03690 0.02660 -0.1134 0.5693 0.7631
4.250 0.8529 0.03910 0.02910 -0.1094 0.5530 0.8198
4.750 0.8725 0.04136 0.03157 -0.1064 0.5373 1.0000
5.000 0.9037 0.04181 0.03194 -0.1073 0.5322 1.0000
5.250 0.9451 0.04155 0.03157 -0.1088 0.5291 1.0000
5.750 0.9553 0.04563 0.03564 -0.1063 0.5119 1.0000
6.000 0.9914 0.04542 0.03537 -0.1068 0.5087 1.0000
6.250 0.9631 0.05042 0.04046 -0.1044 0.4948 1.0000
6.500 1.0011 0.04975 0.03973 -0.1045 0.4921 1.0000
7.000 1.0077 0.05466 0.04469 -0.1026 0.4747 1.0000
7.500 1.0282 0.05781 0.04787 -0.1007 0.4571 1.0000
7.750 1.0793 0.05491 0.04490 -0.1000 0.4548 1.0000
8.000 1.0526 0.06033 0.05040 -0.0987 0.4394 1.0000
8.250 1.1005 0.05760 0.04765 -0.0978 0.4370 1.0000
8.750 1.0545 0.06883 0.05904 -0.0965 0.4088 1.0000
9.000 1.0807 0.06844 0.05867 -0.0955 0.4038 1.0000
9.250 1.1193 0.06653 0.05676 -0.0942 0.4011 1.0000
9.750 1.1299 0.07090 0.06123 -0.0926 0.3829 1.0000
10.250 1.1422 0.07497 0.06541 -0.0911 0.3645 1.0000
10.750 1.1291 0.08260 0.07316 -0.0905 0.3414 1.0000
11.250 1.1594 0.08390 0.07452 -0.0885 0.3257 1.0000
11.750 1.1254 0.09528 0.08605 -0.0897 0.2996 1.0000
12.000 1.1542 0.09369 0.08449 -0.0881 0.2949 1.0000
12.500 1.1609 0.09895 0.08984 -0.0878 0.2777 1.0000
13.000 1.1611 0.10565 0.09664 -0.0883 0.2613 1.0000
13.500 1.1584 0.11307 0.10418 -0.0893 0.2455 1.0000
13.750 1.1905 0.11070 0.10182 -0.0874 0.2429 1.0000
14.000 1.1525 0.12145 0.11267 -0.0913 0.2305 1.0000
14.250 1.1817 0.11943 0.11068 -0.0895 0.2276 1.0000
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