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GOE 535 AIRFOIL (goe535-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
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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