GOE 433 AIRFOIL (goe433-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 433 AIRFOIL (goe433-il) Reynolds number: 100,000 Max Cl/Cd: 48.24 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe433-il-100000.txt Download as CSV file: xf-goe433-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2297 0.12526 0.11987 -0.0414 1.0000 0.1747
-10.750 -0.2612 0.12616 0.12089 -0.0393 1.0000 0.1794
-10.500 -0.3339 0.12953 0.12446 -0.0372 1.0000 0.1808
-10.250 -0.3115 0.12523 0.12018 -0.0339 1.0000 0.1818
-10.000 -0.3024 0.12332 0.11832 -0.0305 1.0000 0.1831
-9.750 -0.2718 0.11993 0.11490 -0.0324 0.9966 0.1869
-9.500 -0.2964 0.11793 0.11292 -0.0438 0.9876 0.1970
-9.250 -0.2530 0.11193 0.10688 -0.0453 0.9842 0.1989
-9.000 -0.2101 0.10786 0.10275 -0.0481 0.9805 0.2025
-8.750 -0.2283 0.10576 0.10066 -0.0586 0.9687 0.2139
-8.500 -0.1821 0.10011 0.09497 -0.0604 0.9664 0.2164
-8.250 -0.1373 0.09632 0.09112 -0.0637 0.9639 0.2209
-8.000 -0.2867 0.06517 0.05976 -0.0992 0.9327 0.1648
-7.750 -0.3074 0.05262 0.04684 -0.1127 0.9169 0.1631
-7.500 -0.3135 0.04243 0.03565 -0.1242 0.9024 0.1649
-7.250 -0.2738 0.04073 0.03404 -0.1269 0.8978 0.1685
-7.000 -0.2452 0.03951 0.03276 -0.1282 0.8897 0.1719
-6.750 -0.2171 0.03689 0.02976 -0.1314 0.8815 0.1763
-6.500 -0.1785 0.03395 0.02626 -0.1361 0.8771 0.1820
-6.250 -0.1585 0.03339 0.02578 -0.1352 0.8665 0.1855
-6.000 -0.1230 0.03227 0.02454 -0.1370 0.8608 0.1910
-5.750 -0.0836 0.03052 0.02238 -0.1399 0.8569 0.1984
-5.500 -0.0659 0.03029 0.02225 -0.1386 0.8456 0.2028
-5.250 -0.0303 0.02933 0.02112 -0.1400 0.8402 0.2106
-5.000 -0.0004 0.02855 0.02026 -0.1405 0.8337 0.2181
-4.750 0.0242 0.02829 0.01999 -0.1402 0.8248 0.2259
-4.500 0.0588 0.02742 0.01900 -0.1412 0.8197 0.2356
-4.250 0.0846 0.02727 0.01884 -0.1409 0.8122 0.2453
-4.000 0.1113 0.02691 0.01847 -0.1409 0.8043 0.2551
-3.750 0.1454 0.02641 0.01780 -0.1416 0.7994 0.2679
-3.500 0.1691 0.02634 0.01789 -0.1409 0.7916 0.2775
-3.250 0.1969 0.02610 0.01754 -0.1410 0.7841 0.2902
-3.000 0.2294 0.02567 0.01714 -0.1412 0.7792 0.3039
-2.750 0.2527 0.02571 0.01727 -0.1407 0.7711 0.3158
-2.500 0.2806 0.02553 0.01708 -0.1406 0.7638 0.3312
-2.250 0.3135 0.02512 0.01666 -0.1408 0.7591 0.3494
-2.000 0.3358 0.02541 0.01703 -0.1401 0.7504 0.3661
-1.750 0.3637 0.02535 0.01708 -0.1397 0.7435 0.3843
-1.500 0.3967 0.02505 0.01679 -0.1396 0.7390 0.4055
-1.250 0.4170 0.02557 0.01745 -0.1385 0.7294 0.4222
-1.000 0.4463 0.02555 0.01745 -0.1381 0.7231 0.4423
-0.750 0.4795 0.02532 0.01720 -0.1379 0.7189 0.4630
-0.500 0.4981 0.02594 0.01794 -0.1367 0.7084 0.4787
-0.250 0.5286 0.02576 0.01775 -0.1363 0.7027 0.4980
0.000 0.5579 0.02571 0.01768 -0.1359 0.6969 0.5163
0.250 0.5798 0.02610 0.01813 -0.1350 0.6876 0.5333
0.500 0.6116 0.02579 0.01779 -0.1348 0.6825 0.5524
0.750 0.6352 0.02609 0.01813 -0.1340 0.6742 0.5701
1.000 0.6619 0.02610 0.01815 -0.1335 0.6667 0.5886
1.250 0.6944 0.02574 0.01776 -0.1333 0.6622 0.6084
1.500 0.7129 0.02639 0.01851 -0.1320 0.6527 0.6268
1.750 0.7401 0.02630 0.01846 -0.1313 0.6462 0.6471
2.000 0.7726 0.02594 0.01805 -0.1309 0.6418 0.6676
2.250 0.7877 0.02678 0.01905 -0.1294 0.6314 0.6831
2.500 0.8163 0.02668 0.01896 -0.1290 0.6257 0.7000
2.750 0.8496 0.02641 0.01863 -0.1289 0.6216 0.7176
3.000 0.8615 0.02748 0.01989 -0.1273 0.6108 0.7320
3.250 0.8916 0.02735 0.01973 -0.1270 0.6054 0.7497
3.500 0.9195 0.02751 0.01989 -0.1267 0.6001 0.7678
3.750 0.9334 0.02855 0.02108 -0.1252 0.5908 0.7850
4.000 0.9622 0.02843 0.02097 -0.1248 0.5856 0.8057
4.250 0.9914 0.02832 0.02086 -0.1243 0.5811 0.8295
4.500 0.9972 0.02964 0.02243 -0.1219 0.5713 0.8574
4.750 1.0222 0.02935 0.02228 -0.1207 0.5664 0.9211
5.000 1.0706 0.02900 0.02175 -0.1240 0.5622 1.0000
5.250 1.0818 0.03069 0.02357 -0.1235 0.5511 1.0000
5.500 1.1255 0.03000 0.02269 -0.1253 0.5455 1.0000
5.750 1.1441 0.03084 0.02354 -0.1245 0.5361 1.0000
6.000 1.1802 0.03016 0.02273 -0.1250 0.5282 1.0000
6.250 1.2097 0.02998 0.02248 -0.1249 0.5200 1.0000
6.500 1.2355 0.02989 0.02234 -0.1242 0.5107 1.0000
6.750 1.2722 0.02924 0.02153 -0.1247 0.5038 1.0000
7.000 1.2868 0.02990 0.02229 -0.1230 0.4941 1.0000
7.250 1.3277 0.02903 0.02123 -0.1240 0.4878 1.0000
7.500 1.3370 0.03005 0.02240 -0.1218 0.4784 1.0000
7.750 1.3699 0.02970 0.02197 -0.1219 0.4716 1.0000
8.000 1.3886 0.03023 0.02254 -0.1206 0.4636 1.0000
8.250 1.4127 0.03029 0.02259 -0.1198 0.4552 1.0000
8.500 1.4380 0.03034 0.02261 -0.1191 0.4468 1.0000
8.750 1.4570 0.03058 0.02287 -0.1177 0.4373 1.0000
9.000 1.4799 0.03074 0.02299 -0.1167 0.4284 1.0000
9.250 1.4975 0.03110 0.02338 -0.1152 0.4190 1.0000
9.500 1.5176 0.03146 0.02373 -0.1140 0.4103 1.0000
9.750 1.5321 0.03198 0.02429 -0.1121 0.4009 1.0000
10.000 1.5487 0.03247 0.02480 -0.1105 0.3919 1.0000
10.250 1.5590 0.03306 0.02543 -0.1080 0.3823 1.0000
10.500 1.5675 0.03379 0.02619 -0.1054 0.3730 1.0000
10.750 1.5785 0.03433 0.02671 -0.1032 0.3627 1.0000
11.000 1.5756 0.03564 0.02813 -0.0998 0.3525 1.0000
11.250 1.5943 0.03589 0.02825 -0.0984 0.3423 1.0000
11.500 1.5810 0.03800 0.03056 -0.0947 0.3319 1.0000
11.750 1.5894 0.03898 0.03151 -0.0928 0.3221 1.0000
12.000 1.5857 0.04084 0.03345 -0.0903 0.3118 1.0000
12.250 1.5856 0.04264 0.03528 -0.0883 0.3019 1.0000
12.500 1.5903 0.04405 0.03666 -0.0866 0.2921 1.0000
12.750 1.5806 0.04682 0.03955 -0.0847 0.2818 1.0000
13.000 1.5847 0.04842 0.04107 -0.0832 0.2722 1.0000
13.250 1.5759 0.05142 0.04419 -0.0817 0.2628 1.0000
13.500 1.5764 0.05358 0.04632 -0.0805 0.2539 1.0000
13.750 1.5711 0.05643 0.04922 -0.0794 0.2451 1.0000
14.000 1.5692 0.05904 0.05185 -0.0784 0.2367 1.0000
14.250 1.5664 0.06179 0.05462 -0.0776 0.2281 1.0000
14.500 1.5607 0.06503 0.05791 -0.0770 0.2196 1.0000
14.750 1.5626 0.06730 0.06008 -0.0762 0.2107 1.0000
15.000 1.5502 0.07159 0.06450 -0.0760 0.2018 1.0000
15.250 1.5500 0.07422 0.06701 -0.0754 0.1924 1.0000
15.500 1.5414 0.07808 0.07091 -0.0752 0.1827 1.0000
15.750 1.5350 0.08174 0.07456 -0.0750 0.1729 1.0000
16.000 1.5389 0.08391 0.07655 -0.0742 0.1633 1.0000
16.250 1.5336 0.08755 0.08023 -0.0741 0.1551 1.0000
16.500 1.5390 0.08972 0.08231 -0.0733 0.1483 1.0000
16.750 1.5383 0.09288 0.08554 -0.0732 0.1428 1.0000
17.000 1.5622 0.09247 0.08487 -0.0716 0.1378 1.0000
17.250 1.5501 0.09738 0.09006 -0.0724 0.1347 1.0000
17.500 1.5476 0.10095 0.09377 -0.0728 0.1316 1.0000
17.750 1.5566 0.10280 0.09563 -0.0724 0.1287 1.0000
18.000 1.5872 0.10160 0.09424 -0.0705 0.1259 1.0000
18.250 1.5793 0.10605 0.09890 -0.0714 0.1244 1.0000
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