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GOE 435 AIRFOIL (goe435-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 435 AIRFOIL (goe435-il)
Reynolds number: 100,000
Max Cl/Cd: 33.13 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe435-il-100000-n5.txt
Download as CSV file: xf-goe435-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 435 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.1789   0.11140   0.10470  -0.0784   0.8664   0.1133
 -13.250  -0.1780   0.10796   0.10125  -0.0798   0.8578   0.1192
 -12.250  -0.3436   0.07052   0.06311  -0.0997   0.8353   0.1695
 -12.000  -0.2865   0.07544   0.06812  -0.0963   0.8265   0.1700
 -11.750  -0.2454   0.07842   0.07111  -0.0940   0.8191   0.1706
 -11.500  -0.2115   0.08033   0.07306  -0.0928   0.8106   0.1717
 -11.250  -0.4341   0.04907   0.04095  -0.1119   0.8081   0.1794
 -11.000  -0.4610   0.04404   0.03560  -0.1153   0.8009   0.1810
 -10.750  -0.4751   0.04063   0.03187  -0.1174   0.7946   0.1826
 -10.500  -0.4819   0.03850   0.02956  -0.1185   0.7865   0.1838
 -10.250  -0.4566   0.03827   0.02940  -0.1179   0.7800   0.1856
 -10.000  -0.4386   0.03771   0.02882  -0.1175   0.7743   0.1872
  -9.750  -0.4230   0.03690   0.02793  -0.1175   0.7694   0.1889
  -9.500  -0.4096   0.03602   0.02702  -0.1180   0.7624   0.1905
  -9.250  -0.3953   0.03512   0.02603  -0.1184   0.7557   0.1923
  -9.000  -0.3797   0.03424   0.02500  -0.1186   0.7498   0.1942
  -8.750  -0.3624   0.03336   0.02393  -0.1189   0.7447   0.1960
  -8.500  -0.3456   0.03265   0.02309  -0.1191   0.7379   0.1975
  -8.250  -0.3269   0.03202   0.02231  -0.1191   0.7307   0.1987
  -8.000  -0.3034   0.03147   0.02172  -0.1190   0.7245   0.1998
  -7.750  -0.2779   0.03100   0.02123  -0.1188   0.7194   0.2012
  -7.500  -0.2543   0.03064   0.02090  -0.1185   0.7134   0.2029
  -7.250  -0.2323   0.03031   0.02059  -0.1182   0.7062   0.2047
  -7.000  -0.2085   0.02990   0.02014  -0.1182   0.6999   0.2065
  -6.750  -0.1833   0.02944   0.01959  -0.1182   0.6947   0.2082
  -6.500  -0.1577   0.02900   0.01906  -0.1184   0.6898   0.2099
  -6.250  -0.1364   0.02871   0.01875  -0.1181   0.6820   0.2116
  -6.000  -0.1120   0.02833   0.01827  -0.1181   0.6753   0.2135
  -5.750  -0.0856   0.02791   0.01777  -0.1182   0.6698   0.2155
  -5.500  -0.0591   0.02756   0.01745  -0.1181   0.6648   0.2177
  -5.250  -0.0371   0.02739   0.01736  -0.1176   0.6571   0.2198
  -5.000  -0.0119   0.02712   0.01710  -0.1175   0.6511   0.2218
  -4.750   0.0153   0.02680   0.01673  -0.1176   0.6463   0.2238
  -4.500   0.0433   0.02650   0.01635  -0.1178   0.6421   0.2256
  -4.250   0.0655   0.02642   0.01631  -0.1173   0.6352   0.2269
  -4.000   0.0911   0.02623   0.01609  -0.1172   0.6294   0.2280
  -3.750   0.1188   0.02597   0.01577  -0.1173   0.6248   0.2293
  -3.500   0.1483   0.02569   0.01540  -0.1176   0.6211   0.2306
  -3.250   0.1700   0.02569   0.01550  -0.1170   0.6145   0.2319
  -3.000   0.1952   0.02557   0.01542  -0.1169   0.6094   0.2336
  -2.750   0.2228   0.02537   0.01524  -0.1171   0.6052   0.2356
  -2.500   0.2524   0.02513   0.01495  -0.1175   0.6017   0.2381
  -2.250   0.2778   0.02507   0.01491  -0.1175   0.5968   0.2409
  -2.000   0.3022   0.02507   0.01495  -0.1173   0.5914   0.2441
  -1.750   0.3295   0.02495   0.01485  -0.1175   0.5870   0.2481
  -1.500   0.3596   0.02468   0.01460  -0.1181   0.5828   0.2541
  -1.250   0.3880   0.02449   0.01443  -0.1184   0.5777   0.2623
  -1.000   0.4112   0.02449   0.01459  -0.1181   0.5704   0.2739
  -0.750   0.4400   0.02436   0.01458  -0.1184   0.5647   0.2931
  -0.500   0.4720   0.02429   0.01454  -0.1189   0.5603   0.3193
  -0.250   0.4956   0.02458   0.01487  -0.1185   0.5547   0.3414
   0.000   0.5208   0.02483   0.01511  -0.1182   0.5494   0.3581
   0.250   0.5491   0.02497   0.01519  -0.1183   0.5447   0.3715
   0.500   0.5810   0.02501   0.01505  -0.1190   0.5407   0.3845
   0.750   0.6069   0.02527   0.01535  -0.1186   0.5362   0.3926
   1.000   0.6286   0.02564   0.01572  -0.1179   0.5306   0.4011
   1.250   0.6544   0.02584   0.01589  -0.1177   0.5255   0.4090
   1.500   0.6830   0.02597   0.01601  -0.1177   0.5211   0.4167
   1.750   0.7165   0.02601   0.01589  -0.1184   0.5171   0.4253
   2.000   0.7329   0.02649   0.01643  -0.1171   0.5112   0.4310
   2.250   0.7539   0.02677   0.01679  -0.1162   0.5056   0.4353
   2.500   0.7804   0.02692   0.01693  -0.1159   0.5006   0.4407
   2.750   0.8126   0.02695   0.01686  -0.1165   0.4963   0.4477
   3.000   0.8303   0.02739   0.01732  -0.1153   0.4905   0.4530
   3.250   0.8470   0.02780   0.01778  -0.1139   0.4843   0.4573
   3.500   0.8703   0.02797   0.01799  -0.1133   0.4788   0.4619
   3.750   0.9010   0.02800   0.01796  -0.1136   0.4741   0.4676
   4.000   0.9129   0.02855   0.01859  -0.1116   0.4679   0.4722
   4.250   0.9219   0.02906   0.01917  -0.1092   0.4611   0.4762
   4.500   0.9440   0.02925   0.01929  -0.1085   0.4554   0.4803
   4.750   0.9713   0.02932   0.01929  -0.1084   0.4504   0.4845
   5.000   0.9698   0.03043   0.02061  -0.1052   0.4426   0.4878
   5.250   0.9859   0.03093   0.02116  -0.1040   0.4360   0.4928
   5.500   1.0148   0.03090   0.02104  -0.1040   0.4310   0.4995
   5.750   1.0098   0.03253   0.02284  -0.1012   0.4222   0.5036
   6.000   1.0256   0.03316   0.02344  -0.1002   0.4155   0.5092
   6.250   1.0407   0.03379   0.02413  -0.0991   0.4093   0.5142
   6.500   1.0416   0.03537   0.02584  -0.0972   0.4008   0.5183
   6.750   1.0621   0.03573   0.02616  -0.0966   0.3950   0.5244
   7.000   1.0632   0.03753   0.02805  -0.0951   0.3868   0.5291
   7.250   1.0757   0.03856   0.02905  -0.0943   0.3801   0.5344
   7.500   1.0925   0.03924   0.02974  -0.0936   0.3745   0.5393
   7.750   1.0935   0.04124   0.03185  -0.0923   0.3668   0.5434
   8.000   1.1120   0.04185   0.03242  -0.0917   0.3615   0.5492
   8.250   1.1227   0.04318   0.03375  -0.0910   0.3556   0.5553
   8.500   1.1276   0.04506   0.03566  -0.0901   0.3491   0.5615
   8.750   1.1469   0.04559   0.03619  -0.0896   0.3445   0.5686
   9.000   1.1619   0.04660   0.03720  -0.0890   0.3398   0.5770
   9.250   1.1622   0.04898   0.03968  -0.0880   0.3338   0.5849
   9.500   1.1761   0.05007   0.04080  -0.0874   0.3292   0.5942
   9.750   1.2019   0.05008   0.04074  -0.0871   0.3256   0.6075
  10.000   1.2022   0.05254   0.04332  -0.0862   0.3206   0.6184
  10.250   1.2045   0.05483   0.04574  -0.0854   0.3157   0.6313
  10.500   1.2181   0.05600   0.04695  -0.0848   0.3119   0.6483
  10.750   1.2428   0.05605   0.04699  -0.0843   0.3089   0.6709
  11.000   1.2519   0.05770   0.04871  -0.0836   0.3052   0.6925
  11.250   1.2403   0.06149   0.05271  -0.0828   0.3003   0.7092
  11.500   1.2455   0.06357   0.05487  -0.0821   0.2964   0.7323
  11.750   1.2625   0.06436   0.05568  -0.0816   0.2933   0.7599
  12.000   1.2886   0.06409   0.05538  -0.0809   0.2910   0.7906
  12.250   1.2859   0.06695   0.05839  -0.0801   0.2876   0.8152
  12.500   1.2505   0.07370   0.06546  -0.0796   0.2823   0.8313
  12.750   1.2420   0.07659   0.06854  -0.0783   0.2786   0.8970
  13.000   1.2568   0.07735   0.06926  -0.0779   0.2761   1.0000
  13.250   1.2859   0.07702   0.06881  -0.0778   0.2742   1.0000
  13.750   1.1509   0.10133   0.09376  -0.0810   0.2588   1.0000
  14.000   1.1795   0.10078   0.09312  -0.0807   0.2577   1.0000
  14.250   1.2123   0.09962   0.09185  -0.0803   0.2568   1.0000
  14.500   1.2480   0.09808   0.09020  -0.0798   0.2560   1.0000
  15.000   0.9311   0.15820   0.15137  -0.1000   0.2173   1.0000
  15.250   0.9400   0.16080   0.15395  -0.1013   0.2148   1.0000
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