GOE 535 AIRFOIL (goe535-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 535 AIRFOIL (goe535-il) Reynolds number: 100,000 Max Cl/Cd: 43.14 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe535-il-100000.txt Download as CSV file: xf-goe535-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2030 0.12288 0.11781 -0.0330 1.0000 0.1275
-10.000 -0.2192 0.12225 0.11729 -0.0323 1.0000 0.1311
-9.750 -0.2739 0.12437 0.11959 -0.0328 1.0000 0.1326
-9.500 -0.2548 0.12015 0.11542 -0.0294 1.0000 0.1336
-9.250 -0.2472 0.11820 0.11354 -0.0260 1.0000 0.1350
-9.000 -0.2533 0.11753 0.11297 -0.0227 1.0000 0.1364
-8.750 -0.2253 0.11369 0.10911 -0.0282 0.9942 0.1418
-8.500 -0.2284 0.10980 0.10524 -0.0392 0.9840 0.1473
-8.250 -0.1778 0.10531 0.10071 -0.0402 0.9806 0.1513
-8.000 -0.2001 0.10386 0.09930 -0.0546 0.9639 0.1614
-7.750 -0.1392 0.09758 0.09299 -0.0525 0.9630 0.1642
-7.500 -0.1046 0.09409 0.08949 -0.0553 0.9548 0.1697
-7.250 -0.1170 0.09098 0.08641 -0.0650 0.9384 0.1786
-7.000 -0.0607 0.08652 0.08191 -0.0658 0.9364 0.1831
-6.750 -0.0776 0.08383 0.07925 -0.0771 0.9172 0.1953
-6.500 -0.0125 0.07948 0.07486 -0.0748 0.9179 0.2005
-6.250 -0.1047 0.05024 0.04480 -0.1162 0.8841 0.1332
-6.000 -0.0631 0.04478 0.03916 -0.1226 0.8797 0.1297
-5.750 -0.0450 0.03955 0.03339 -0.1270 0.8658 0.1289
-5.500 -0.0025 0.03484 0.02797 -0.1331 0.8602 0.1306
-5.250 0.0225 0.03256 0.02511 -0.1339 0.8469 0.1325
-5.000 0.0653 0.03029 0.02288 -0.1366 0.8407 0.1372
-4.750 0.0924 0.02896 0.02134 -0.1366 0.8275 0.1408
-4.500 0.1348 0.02727 0.01912 -0.1389 0.8200 0.1461
-4.250 0.1599 0.02604 0.01789 -0.1383 0.8061 0.1501
-4.000 0.1997 0.02486 0.01656 -0.1398 0.7976 0.1564
-3.750 0.2256 0.02421 0.01562 -0.1390 0.7829 0.1610
-3.500 0.2548 0.02325 0.01473 -0.1388 0.7705 0.1667
-3.250 0.2878 0.02255 0.01387 -0.1390 0.7591 0.1737
-3.000 0.3130 0.02204 0.01328 -0.1380 0.7451 0.1796
-2.750 0.3451 0.02143 0.01267 -0.1381 0.7343 0.1885
-2.500 0.3700 0.02106 0.01224 -0.1371 0.7203 0.1968
-2.250 0.3966 0.02072 0.01194 -0.1364 0.7083 0.2088
-2.000 0.4245 0.02029 0.01156 -0.1359 0.6970 0.2258
-1.750 0.4482 0.01997 0.01143 -0.1349 0.6849 0.2549
-1.500 0.4761 0.01984 0.01180 -0.1342 0.6748 0.3695
-1.250 0.4978 0.02070 0.01274 -0.1320 0.6629 0.4356
-1.000 0.5254 0.02132 0.01328 -0.1307 0.6537 0.4684
-0.750 0.5471 0.02190 0.01388 -0.1290 0.6430 0.4903
-0.500 0.5737 0.02225 0.01413 -0.1278 0.6340 0.5097
-0.250 0.5970 0.02263 0.01449 -0.1265 0.6247 0.5265
0.000 0.6214 0.02288 0.01468 -0.1253 0.6157 0.5428
0.250 0.6494 0.02312 0.01480 -0.1246 0.6088 0.5620
0.500 0.6680 0.02346 0.01523 -0.1226 0.5991 0.5802
0.750 0.6940 0.02354 0.01524 -0.1216 0.5920 0.6000
1.000 0.7169 0.02378 0.01546 -0.1204 0.5845 0.6169
1.250 0.7389 0.02393 0.01564 -0.1192 0.5764 0.6311
1.500 0.7678 0.02388 0.01548 -0.1189 0.5702 0.6438
1.750 0.7901 0.02421 0.01580 -0.1180 0.5625 0.6541
2.000 0.8139 0.02432 0.01593 -0.1172 0.5551 0.6624
2.250 0.8458 0.02438 0.01580 -0.1177 0.5493 0.6712
2.500 0.8656 0.02473 0.01624 -0.1165 0.5418 0.6779
2.750 0.8900 0.02493 0.01643 -0.1158 0.5347 0.6866
3.000 0.9225 0.02498 0.01632 -0.1164 0.5291 0.6955
3.250 0.9431 0.02546 0.01689 -0.1154 0.5216 0.7035
3.500 0.9691 0.02574 0.01715 -0.1151 0.5145 0.7133
3.750 1.0031 0.02575 0.01703 -0.1158 0.5088 0.7253
4.000 1.0224 0.02632 0.01773 -0.1147 0.5012 0.7369
4.250 1.0486 0.02655 0.01799 -0.1144 0.4940 0.7514
4.500 1.0841 0.02652 0.01785 -0.1154 0.4884 0.7702
4.750 1.1009 0.02711 0.01872 -0.1139 0.4807 0.7956
5.000 1.1344 0.02704 0.01889 -0.1150 0.4733 1.0000
5.250 1.1741 0.02730 0.01886 -0.1170 0.4678 1.0000
5.500 1.1866 0.02832 0.02003 -0.1152 0.4599 1.0000
5.750 1.2141 0.02875 0.02036 -0.1152 0.4532 1.0000
6.000 1.2519 0.02902 0.02035 -0.1166 0.4480 1.0000
6.250 1.2589 0.03016 0.02171 -0.1138 0.4401 1.0000
6.500 1.2844 0.03058 0.02206 -0.1134 0.4335 1.0000
6.750 1.3219 0.03080 0.02202 -0.1146 0.4282 1.0000
7.000 1.3244 0.03210 0.02357 -0.1112 0.4205 1.0000
7.250 1.3480 0.03260 0.02404 -0.1105 0.4142 1.0000
7.500 1.3869 0.03276 0.02396 -0.1118 0.4091 1.0000
7.750 1.3841 0.03426 0.02574 -0.1078 0.4014 1.0000
8.000 1.4062 0.03475 0.02620 -0.1068 0.3950 1.0000
8.250 1.4474 0.03479 0.02600 -0.1085 0.3899 1.0000
8.500 1.4379 0.03658 0.02811 -0.1036 0.3827 1.0000
8.750 1.4554 0.03731 0.02886 -0.1022 0.3767 1.0000
9.000 1.4959 0.03729 0.02865 -0.1037 0.3718 1.0000
9.250 1.4852 0.03928 0.03091 -0.0989 0.3655 1.0000
9.500 1.4917 0.04041 0.03214 -0.0962 0.3594 1.0000
9.750 1.5309 0.04025 0.03183 -0.0974 0.3545 1.0000
10.000 1.5316 0.04190 0.03361 -0.0942 0.3493 1.0000
10.250 1.5055 0.04438 0.03632 -0.0879 0.3440 1.0000
10.500 1.5204 0.04523 0.03718 -0.0864 0.3393 1.0000
10.750 1.5925 0.04416 0.03587 -0.0914 0.3347 1.0000
11.000 1.5174 0.04885 0.04097 -0.0805 0.3307 1.0000
11.250 1.2390 0.07741 0.07013 -0.0734 0.3177 1.0000
11.500 1.3591 0.06544 0.05806 -0.0708 0.3191 1.0000
11.750 1.5865 0.05002 0.04208 -0.0786 0.3162 1.0000
12.000 0.9485 0.14060 0.13370 -0.0959 0.2987 1.0000
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Polar data table (+)
Polar graphs
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