GOE 535 AIRFOIL (goe535-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 535 AIRFOIL (goe535-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.19 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe535-il-1000000-n5.txt Download as CSV file: xf-goe535-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.6843 0.10255 0.09983 -0.0646 1.0000 0.0272
-17.000 -0.7212 0.09317 0.09033 -0.0701 1.0000 0.0273
-16.750 -0.7590 0.08405 0.08108 -0.0756 1.0000 0.0273
-16.500 -0.7951 0.07562 0.07252 -0.0807 1.0000 0.0274
-16.250 -0.8295 0.06791 0.06470 -0.0852 1.0000 0.0274
-16.000 -0.8622 0.06082 0.05749 -0.0891 1.0000 0.0275
-15.750 -0.8948 0.05438 0.05095 -0.0923 1.0000 0.0275
-15.250 -0.9158 0.04250 0.03884 -0.1053 0.9961 0.0278
-15.000 -0.9193 0.03772 0.03395 -0.1112 0.9909 0.0279
-14.750 -0.9210 0.03347 0.02961 -0.1165 0.9841 0.0280
-14.500 -0.9065 0.02941 0.02545 -0.1238 0.9799 0.0282
-14.250 -0.8927 0.02628 0.02223 -0.1286 0.9728 0.0284
-14.000 -0.8655 0.02356 0.01941 -0.1345 0.9689 0.0286
-13.750 -0.8316 0.02145 0.01722 -0.1400 0.9668 0.0289
-13.500 -0.8016 0.02005 0.01573 -0.1431 0.9631 0.0291
-13.250 -0.7731 0.01905 0.01466 -0.1448 0.9579 0.0294
-13.000 -0.7407 0.01818 0.01373 -0.1469 0.9539 0.0297
-12.750 -0.7075 0.01740 0.01289 -0.1490 0.9500 0.0300
-12.500 -0.6810 0.01677 0.01220 -0.1494 0.9424 0.0304
-12.250 -0.6488 0.01617 0.01153 -0.1508 0.9347 0.0307
-12.000 -0.6210 0.01565 0.01093 -0.1512 0.9218 0.0309
-11.750 -0.5936 0.01509 0.01027 -0.1515 0.9041 0.0313
-11.500 -0.5682 0.01459 0.00968 -0.1513 0.8835 0.0317
-11.250 -0.5436 0.01419 0.00918 -0.1509 0.8639 0.0321
-11.000 -0.5192 0.01384 0.00873 -0.1503 0.8450 0.0325
-10.750 -0.4952 0.01353 0.00831 -0.1495 0.8235 0.0330
-10.500 -0.4714 0.01327 0.00793 -0.1487 0.8000 0.0334
-10.250 -0.4471 0.01302 0.00757 -0.1480 0.7794 0.0339
-10.000 -0.4223 0.01279 0.00723 -0.1473 0.7613 0.0344
-9.750 -0.3972 0.01258 0.00691 -0.1466 0.7436 0.0348
-9.500 -0.3723 0.01232 0.00658 -0.1459 0.7269 0.0355
-9.250 -0.3471 0.01210 0.00628 -0.1453 0.7114 0.0362
-9.000 -0.3209 0.01188 0.00600 -0.1448 0.6989 0.0371
-8.750 -0.2947 0.01169 0.00574 -0.1443 0.6875 0.0379
-8.500 -0.2681 0.01150 0.00549 -0.1438 0.6757 0.0388
-8.250 -0.2418 0.01131 0.00525 -0.1433 0.6644 0.0399
-8.000 -0.2152 0.01114 0.00503 -0.1428 0.6521 0.0412
-7.750 -0.1883 0.01099 0.00482 -0.1423 0.6419 0.0426
-7.500 -0.1613 0.01084 0.00462 -0.1419 0.6318 0.0439
-7.250 -0.1343 0.01069 0.00445 -0.1414 0.6226 0.0454
-7.000 -0.1070 0.01057 0.00428 -0.1410 0.6125 0.0470
-6.750 -0.0800 0.01047 0.00412 -0.1405 0.6020 0.0485
-6.500 -0.0527 0.01036 0.00398 -0.1401 0.5910 0.0502
-6.250 -0.0255 0.01028 0.00385 -0.1397 0.5811 0.0518
-6.000 0.0021 0.01019 0.00371 -0.1393 0.5712 0.0532
-5.750 0.0292 0.01012 0.00361 -0.1388 0.5614 0.0549
-5.500 0.0569 0.01005 0.00350 -0.1384 0.5509 0.0565
-5.250 0.0841 0.01002 0.00341 -0.1380 0.5394 0.0582
-5.000 0.1114 0.00996 0.00331 -0.1375 0.5274 0.0596
-4.750 0.1387 0.00992 0.00323 -0.1371 0.5171 0.0612
-4.500 0.1662 0.00989 0.00315 -0.1367 0.5064 0.0626
-4.250 0.1936 0.00987 0.00307 -0.1362 0.4964 0.0639
-4.000 0.2208 0.00986 0.00300 -0.1358 0.4852 0.0650
-3.750 0.2481 0.00982 0.00293 -0.1353 0.4757 0.0666
-3.500 0.2755 0.00980 0.00287 -0.1349 0.4667 0.0681
-3.250 0.3029 0.00979 0.00283 -0.1345 0.4591 0.0696
-3.000 0.3306 0.00979 0.00278 -0.1341 0.4518 0.0710
-2.750 0.3577 0.00977 0.00273 -0.1337 0.4439 0.0730
-2.500 0.3852 0.00974 0.00269 -0.1333 0.4377 0.0747
-2.250 0.4129 0.00972 0.00265 -0.1329 0.4321 0.0762
-2.000 0.4402 0.00973 0.00262 -0.1325 0.4262 0.0776
-1.750 0.4675 0.00975 0.00260 -0.1320 0.4203 0.0786
-1.500 0.4951 0.00971 0.00256 -0.1316 0.4157 0.0806
-1.250 0.5226 0.00970 0.00253 -0.1313 0.4110 0.0828
-1.000 0.5498 0.00971 0.00253 -0.1308 0.4063 0.0848
-0.750 0.5769 0.00975 0.00253 -0.1304 0.4011 0.0865
-0.500 0.6045 0.00972 0.00252 -0.1300 0.3977 0.0896
-0.250 0.6320 0.00972 0.00252 -0.1296 0.3936 0.0937
0.000 0.6591 0.00972 0.00252 -0.1292 0.3894 0.0994
0.250 0.6857 0.00974 0.00254 -0.1287 0.3845 0.1099
0.500 0.7124 0.00967 0.00256 -0.1282 0.3806 0.1422
0.750 0.7391 0.00954 0.00257 -0.1278 0.3772 0.1932
1.250 0.7907 0.00934 0.00265 -0.1267 0.3660 0.3219
1.500 0.8171 0.00938 0.00274 -0.1262 0.3603 0.3507
1.750 0.8439 0.00944 0.00281 -0.1257 0.3554 0.3662
2.000 0.8702 0.00951 0.00291 -0.1252 0.3504 0.3814
2.250 0.8963 0.00962 0.00300 -0.1246 0.3460 0.3898
2.500 0.9228 0.00969 0.00309 -0.1241 0.3427 0.3986
2.750 0.9494 0.00977 0.00317 -0.1236 0.3391 0.4069
3.000 0.9755 0.00987 0.00326 -0.1230 0.3346 0.4125
3.250 1.0008 0.00999 0.00338 -0.1223 0.3292 0.4197
3.500 1.0264 0.01011 0.00349 -0.1216 0.3249 0.4279
3.750 1.0524 0.01020 0.00359 -0.1211 0.3213 0.4324
4.000 1.0777 0.01031 0.00370 -0.1204 0.3168 0.4380
4.250 1.1024 0.01045 0.00383 -0.1196 0.3120 0.4445
4.500 1.1271 0.01059 0.00397 -0.1188 0.3077 0.4511
4.750 1.1521 0.01070 0.00409 -0.1181 0.3036 0.4554
5.000 1.1762 0.01084 0.00423 -0.1172 0.2980 0.4608
5.250 1.1992 0.01103 0.00440 -0.1162 0.2921 0.4659
5.500 1.2232 0.01117 0.00454 -0.1153 0.2876 0.4710
5.750 1.2463 0.01133 0.00470 -0.1143 0.2822 0.4757
6.000 1.2672 0.01153 0.00488 -0.1128 0.2765 0.4811
6.250 1.2881 0.01169 0.00505 -0.1114 0.2706 0.4873
6.500 1.3076 0.01191 0.00525 -0.1097 0.2627 0.4935
6.750 1.3273 0.01215 0.00547 -0.1081 0.2562 0.4988
7.000 1.3474 0.01236 0.00569 -0.1066 0.2505 0.5054
7.250 1.3660 0.01264 0.00595 -0.1048 0.2442 0.5126
7.500 1.3855 0.01290 0.00620 -0.1032 0.2380 0.5193
7.750 1.4032 0.01321 0.00650 -0.1014 0.2304 0.5262
8.000 1.4208 0.01353 0.00681 -0.0996 0.2233 0.5333
8.250 1.4385 0.01385 0.00712 -0.0978 0.2167 0.5394
8.500 1.4553 0.01420 0.00746 -0.0959 0.2113 0.5453
8.750 1.4729 0.01452 0.00779 -0.0942 0.2056 0.5519
9.000 1.4896 0.01488 0.00815 -0.0924 0.2009 0.5581
9.250 1.5050 0.01529 0.00856 -0.0904 0.1951 0.5639
9.500 1.5218 0.01565 0.00894 -0.0887 0.1907 0.5708
9.750 1.5365 0.01611 0.00939 -0.0867 0.1862 0.5772
10.000 1.5517 0.01655 0.00985 -0.0849 0.1824 0.5841
10.250 1.5677 0.01695 0.01030 -0.0831 0.1795 0.5924
10.500 1.5819 0.01745 0.01081 -0.0813 0.1752 0.6013
10.750 1.5943 0.01803 0.01142 -0.0792 0.1710 0.6126
11.000 1.6080 0.01857 0.01201 -0.0774 0.1676 0.6267
11.250 1.6213 0.01910 0.01262 -0.0755 0.1643 0.6552
12.250 1.7456 0.02226 0.01629 -0.0842 0.1453 1.0000
12.500 1.7581 0.02318 0.01724 -0.0829 0.1423 1.0000
12.750 1.7712 0.02409 0.01818 -0.0817 0.1394 1.0000
13.000 1.7812 0.02526 0.01936 -0.0803 0.1353 1.0000
13.250 1.7891 0.02661 0.02072 -0.0789 0.1313 1.0000
13.500 1.7985 0.02789 0.02204 -0.0777 0.1272 1.0000
13.750 1.8027 0.02965 0.02379 -0.0764 0.1215 1.0000
14.000 1.8073 0.03144 0.02559 -0.0752 0.1153 1.0000
14.250 1.8057 0.03383 0.02797 -0.0738 0.1073 1.0000
14.500 1.7987 0.03685 0.03096 -0.0726 0.0972 1.0000
14.750 1.7880 0.04033 0.03443 -0.0714 0.0875 1.0000
15.000 1.7810 0.04360 0.03773 -0.0706 0.0819 1.0000
15.250 1.7707 0.04734 0.04150 -0.0699 0.0763 1.0000
15.500 1.7650 0.05066 0.04487 -0.0695 0.0729 1.0000
15.750 1.7571 0.05433 0.04859 -0.0692 0.0700 1.0000
16.000 1.7511 0.05785 0.05217 -0.0690 0.0678 1.0000
16.250 1.7458 0.06132 0.05571 -0.0689 0.0662 1.0000
16.500 1.7372 0.06527 0.05972 -0.0690 0.0644 1.0000
16.750 1.7283 0.06934 0.06386 -0.0691 0.0630 1.0000
17.000 1.7207 0.07327 0.06787 -0.0693 0.0619 1.0000
17.250 1.7135 0.07720 0.07188 -0.0696 0.0610 1.0000
17.500 1.7062 0.08118 0.07593 -0.0700 0.0602 1.0000
17.750 1.6982 0.08526 0.08009 -0.0705 0.0593 1.0000
18.000 1.6876 0.08972 0.08463 -0.0711 0.0585 1.0000
18.250 1.6773 0.09418 0.08916 -0.0717 0.0578 1.0000
18.500 1.6685 0.09846 0.09350 -0.0724 0.0570 1.0000
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