GOE 535 AIRFOIL (goe535-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 535 AIRFOIL (goe535-il) Reynolds number: 200,000 Max Cl/Cd: 68.52 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe535-il-200000-n5.txt Download as CSV file: xf-goe535-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 535 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2470 0.09931 0.09528 -0.0556 0.9907 0.0434
-10.500 -0.4916 0.03610 0.03089 -0.1191 0.9509 0.0468
-10.250 -0.4792 0.03103 0.02522 -0.1264 0.9381 0.0480
-10.000 -0.4417 0.02997 0.02415 -0.1297 0.9338 0.0487
-9.750 -0.4171 0.02894 0.02306 -0.1305 0.9216 0.0493
-9.500 -0.3847 0.02767 0.02166 -0.1330 0.9127 0.0502
-9.250 -0.3565 0.02622 0.02002 -0.1346 0.9013 0.0513
-9.000 -0.3293 0.02460 0.01810 -0.1361 0.8902 0.0526
-8.750 -0.2974 0.02356 0.01693 -0.1376 0.8800 0.0537
-8.500 -0.2682 0.02295 0.01627 -0.1382 0.8673 0.0546
-8.250 -0.2362 0.02224 0.01545 -0.1394 0.8553 0.0558
-8.000 -0.2070 0.02140 0.01440 -0.1401 0.8410 0.0577
-7.750 -0.1786 0.02070 0.01354 -0.1404 0.8258 0.0592
-7.500 -0.1494 0.02028 0.01306 -0.1407 0.8109 0.0605
-7.250 -0.1208 0.01979 0.01242 -0.1408 0.7961 0.0621
-7.000 -0.0942 0.01920 0.01161 -0.1406 0.7802 0.0641
-6.750 -0.0676 0.01878 0.01109 -0.1403 0.7649 0.0656
-6.500 -0.0408 0.01848 0.01071 -0.1400 0.7505 0.0672
-6.250 -0.0144 0.01814 0.01022 -0.1396 0.7366 0.0694
-6.000 0.0117 0.01777 0.00968 -0.1392 0.7236 0.0716
-5.750 0.0377 0.01748 0.00933 -0.1387 0.7108 0.0732
-5.500 0.0635 0.01721 0.00899 -0.1381 0.6976 0.0754
-5.250 0.0897 0.01696 0.00859 -0.1376 0.6855 0.0778
-5.000 0.1154 0.01666 0.00822 -0.1370 0.6735 0.0799
-4.750 0.1413 0.01642 0.00795 -0.1365 0.6625 0.0821
-4.500 0.1673 0.01621 0.00765 -0.1359 0.6510 0.0847
-4.250 0.1934 0.01602 0.00734 -0.1353 0.6396 0.0871
-4.000 0.2188 0.01576 0.00706 -0.1347 0.6281 0.0894
-3.750 0.2447 0.01556 0.00683 -0.1341 0.6170 0.0919
-3.500 0.2707 0.01541 0.00658 -0.1335 0.6066 0.0946
-3.250 0.2966 0.01521 0.00635 -0.1329 0.5960 0.0970
-3.000 0.3221 0.01505 0.00614 -0.1323 0.5853 0.0997
-2.750 0.3482 0.01491 0.00597 -0.1317 0.5744 0.1028
-2.500 0.3740 0.01484 0.00579 -0.1310 0.5641 0.1059
-2.250 0.4001 0.01468 0.00563 -0.1305 0.5542 0.1094
-2.000 0.4259 0.01461 0.00550 -0.1299 0.5445 0.1136
-1.750 0.4521 0.01453 0.00538 -0.1293 0.5349 0.1187
-1.500 0.4779 0.01445 0.00528 -0.1287 0.5253 0.1259
-1.250 0.5040 0.01437 0.00519 -0.1282 0.5168 0.1369
-1.000 0.5299 0.01425 0.00513 -0.1276 0.5084 0.1621
-0.750 0.5552 0.01406 0.00506 -0.1271 0.5008 0.2181
-0.500 0.5806 0.01387 0.00519 -0.1266 0.4929 0.3096
-0.250 0.6063 0.01397 0.00532 -0.1259 0.4853 0.3567
0.000 0.6325 0.01411 0.00542 -0.1253 0.4789 0.3813
0.250 0.6588 0.01424 0.00554 -0.1247 0.4721 0.3984
0.500 0.6847 0.01439 0.00564 -0.1240 0.4656 0.4129
0.750 0.7106 0.01458 0.00577 -0.1233 0.4599 0.4280
1.000 0.7366 0.01472 0.00594 -0.1227 0.4539 0.4404
1.250 0.7626 0.01490 0.00606 -0.1221 0.4482 0.4531
1.500 0.7877 0.01509 0.00624 -0.1213 0.4428 0.4640
1.750 0.8137 0.01529 0.00639 -0.1207 0.4377 0.4760
2.000 0.8391 0.01544 0.00660 -0.1200 0.4323 0.4857
2.250 0.8645 0.01563 0.00674 -0.1193 0.4271 0.4950
2.500 0.8896 0.01583 0.00688 -0.1185 0.4222 0.5015
2.750 0.9150 0.01597 0.00705 -0.1179 0.4172 0.5064
3.000 0.9402 0.01612 0.00720 -0.1172 0.4119 0.5112
3.250 0.9649 0.01630 0.00733 -0.1164 0.4063 0.5166
3.500 0.9892 0.01653 0.00747 -0.1157 0.4012 0.5219
3.750 1.0138 0.01664 0.00767 -0.1149 0.3956 0.5266
4.000 1.0380 0.01681 0.00785 -0.1141 0.3900 0.5318
4.250 1.0618 0.01702 0.00802 -0.1132 0.3850 0.5376
4.500 1.0857 0.01724 0.00822 -0.1124 0.3805 0.5429
4.750 1.1096 0.01740 0.00845 -0.1116 0.3754 0.5484
5.000 1.1329 0.01759 0.00867 -0.1106 0.3703 0.5550
5.250 1.1555 0.01783 0.00888 -0.1096 0.3657 0.5619
5.500 1.1778 0.01806 0.00912 -0.1085 0.3616 0.5688
5.750 1.2004 0.01825 0.00939 -0.1075 0.3567 0.5767
6.000 1.2222 0.01847 0.00965 -0.1064 0.3516 0.5837
6.250 1.2435 0.01872 0.00990 -0.1052 0.3466 0.5915
6.500 1.2651 0.01899 0.01019 -0.1041 0.3420 0.6000
6.750 1.2864 0.01921 0.01050 -0.1030 0.3366 0.6090
7.000 1.3063 0.01947 0.01080 -0.1016 0.3316 0.6190
7.250 1.3255 0.01978 0.01111 -0.1001 0.3271 0.6315
7.500 1.3460 0.02005 0.01150 -0.0990 0.3223 0.6477
7.750 1.3659 0.02032 0.01191 -0.0977 0.3170 0.6731
8.000 1.3957 0.02037 0.01233 -0.0986 0.3112 1.0000
8.250 1.4126 0.02080 0.01276 -0.0969 0.3062 1.0000
8.500 1.4294 0.02123 0.01322 -0.0952 0.3006 1.0000
8.750 1.4445 0.02173 0.01371 -0.0934 0.2953 1.0000
9.000 1.4592 0.02227 0.01423 -0.0915 0.2905 1.0000
9.250 1.4748 0.02280 0.01480 -0.0899 0.2847 1.0000
9.500 1.4879 0.02342 0.01543 -0.0879 0.2791 1.0000
9.750 1.5000 0.02411 0.01610 -0.0860 0.2739 1.0000
10.000 1.5134 0.02479 0.01683 -0.0843 0.2677 1.0000
10.250 1.5241 0.02560 0.01764 -0.0823 0.2620 1.0000
10.500 1.5346 0.02648 0.01852 -0.0805 0.2569 1.0000
10.750 1.5459 0.02735 0.01945 -0.0788 0.2509 1.0000
11.000 1.5547 0.02840 0.02050 -0.0770 0.2458 1.0000
11.250 1.5634 0.02950 0.02161 -0.0753 0.2411 1.0000
11.500 1.5732 0.03060 0.02279 -0.0739 0.2358 1.0000
11.750 1.5809 0.03187 0.02408 -0.0724 0.2313 1.0000
12.000 1.5864 0.03333 0.02552 -0.0708 0.2272 1.0000
12.250 1.5955 0.03463 0.02692 -0.0696 0.2228 1.0000
12.500 1.6013 0.03620 0.02855 -0.0684 0.2179 1.0000
12.750 1.6053 0.03796 0.03032 -0.0672 0.2139 1.0000
13.000 1.6102 0.03973 0.03214 -0.0661 0.2097 1.0000
13.250 1.6151 0.04156 0.03405 -0.0652 0.2053 1.0000
13.500 1.6168 0.04372 0.03625 -0.0643 0.2008 1.0000
13.750 1.6174 0.04603 0.03858 -0.0635 0.1970 1.0000
14.000 1.6218 0.04811 0.04077 -0.0630 0.1934 1.0000
14.250 1.6243 0.05041 0.04315 -0.0624 0.1898 1.0000
14.500 1.6250 0.05293 0.04572 -0.0620 0.1864 1.0000
14.750 1.6242 0.05565 0.04845 -0.0616 0.1833 1.0000
15.000 1.6261 0.05820 0.05112 -0.0614 0.1802 1.0000
15.250 1.6262 0.06099 0.05402 -0.0613 0.1767 1.0000
15.500 1.6244 0.06406 0.05716 -0.0613 0.1733 1.0000
15.750 1.6210 0.06732 0.06044 -0.0614 0.1700 1.0000
16.000 1.6192 0.07053 0.06377 -0.0617 0.1667 1.0000
16.250 1.6162 0.07397 0.06732 -0.0620 0.1630 1.0000
16.500 1.6109 0.07773 0.07115 -0.0626 0.1592 1.0000
16.750 1.6051 0.08156 0.07501 -0.0632 0.1557 1.0000
17.000 1.5997 0.08555 0.07916 -0.0640 0.1517 1.0000
17.250 1.5924 0.08980 0.08350 -0.0649 0.1475 1.0000
17.500 1.5850 0.09404 0.08776 -0.0659 0.1437 1.0000
17.750 1.5770 0.09859 0.09246 -0.0672 0.1393 1.0000
18.000 1.5671 0.10340 0.09735 -0.0686 0.1346 1.0000
18.250 1.5581 0.10812 0.10214 -0.0701 0.1301 1.0000
18.500 1.5469 0.11329 0.10741 -0.0719 0.1246 1.0000
18.750 1.5359 0.11843 0.11260 -0.0737 0.1196 1.0000
19.000 1.5241 0.12377 0.11803 -0.0758 0.1138 1.0000
19.250 1.5127 0.12908 0.12338 -0.0780 0.1086 1.0000
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Polar data table (+)
Polar graphs
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