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GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 195 AIRFOIL (goe195-il)
Reynolds number: 50,000
Max Cl/Cd: 44.03 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe195-il-50000-n5.txt
Download as CSV file: xf-goe195-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 195 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3237   0.10652   0.09954  -0.0293   1.0000   0.1347
  -7.750  -0.3422   0.10661   0.09981  -0.0289   1.0000   0.1361
  -7.500  -0.3453   0.10410   0.09742  -0.0286   1.0000   0.1371
  -7.250  -0.3312   0.09968   0.09299  -0.0261   1.0000   0.1395
  -7.000  -0.3298   0.09721   0.09059  -0.0248   1.0000   0.1414
  -6.750  -0.3308   0.09499   0.08846  -0.0240   1.0000   0.1432
  -6.500  -0.3327   0.09283   0.08638  -0.0235   1.0000   0.1446
  -6.000  -0.3363   0.08341   0.07699  -0.0323   1.0000   0.0901
  -5.750  -0.3319   0.08047   0.07409  -0.0323   1.0000   0.0879
  -5.250  -0.3021   0.06898   0.06245  -0.0484   1.0000   0.0780
  -5.000  -0.2914   0.06615   0.05962  -0.0485   1.0000   0.0770
  -4.750  -0.2761   0.06272   0.05616  -0.0506   1.0000   0.0757
  -4.500  -0.2347   0.05695   0.05017  -0.0600   0.9950   0.0736
  -4.250  -0.1815   0.04967   0.04249  -0.0726   0.9893   0.0723
  -4.000  -0.1244   0.04281   0.03501  -0.0851   0.9850   0.0738
  -3.750  -0.0740   0.03773   0.02923  -0.0935   0.9798   0.0737
  -3.500  -0.0249   0.03400   0.02477  -0.1000   0.9752   0.0738
  -3.250   0.0183   0.03149   0.02167  -0.1042   0.9689   0.0745
  -3.000   0.0619   0.02966   0.01931  -0.1079   0.9631   0.0761
  -2.750   0.0997   0.02838   0.01767  -0.1103   0.9551   0.0793
  -2.500   0.1408   0.02735   0.01652  -0.1133   0.9486   0.0832
  -2.250   0.1761   0.02651   0.01548  -0.1149   0.9391   0.0862
  -2.000   0.2188   0.02573   0.01443  -0.1176   0.9327   0.0903
  -1.750   0.2534   0.02515   0.01374  -0.1190   0.9221   0.0956
  -1.500   0.2931   0.02458   0.01309  -0.1212   0.9137   0.1073
  -1.250   0.3326   0.02389   0.01266  -0.1236   0.9047   0.1456
  -1.000   0.3679   0.02371   0.01274  -0.1249   0.8939   0.2518
  -0.750   0.4050   0.02367   0.01280  -0.1266   0.8846   0.3397
  -0.500   0.4374   0.02352   0.01277  -0.1273   0.8733   0.3944
  -0.250   0.4677   0.02337   0.01275  -0.1274   0.8611   0.4410
   0.000   0.4998   0.02314   0.01255  -0.1279   0.8496   0.4718
   0.250   0.5339   0.02283   0.01227  -0.1286   0.8392   0.5036
   0.500   0.5657   0.02248   0.01204  -0.1289   0.8277   0.5466
   0.750   0.5939   0.02206   0.01188  -0.1286   0.8150   0.6192
   1.000   0.6186   0.02133   0.01157  -0.1272   0.8019   1.0000
   1.250   0.6511   0.02143   0.01143  -0.1277   0.7900   1.0000
   1.500   0.6848   0.02147   0.01126  -0.1282   0.7796   1.0000
   1.750   0.7146   0.02165   0.01130  -0.1282   0.7670   1.0000
   2.000   0.7433   0.02188   0.01142  -0.1281   0.7544   1.0000
   2.250   0.7726   0.02210   0.01153  -0.1280   0.7424   1.0000
   2.500   0.8034   0.02224   0.01158  -0.1280   0.7316   1.0000
   2.750   0.8315   0.02250   0.01180  -0.1277   0.7192   1.0000
   3.000   0.8579   0.02283   0.01210  -0.1272   0.7060   1.0000
   3.250   0.8846   0.02314   0.01239  -0.1266   0.6930   1.0000
   3.500   0.9114   0.02342   0.01267  -0.1260   0.6799   1.0000
   3.750   0.9382   0.02367   0.01291  -0.1254   0.6668   1.0000
   4.000   0.9652   0.02391   0.01314  -0.1247   0.6539   1.0000
   4.250   0.9898   0.02426   0.01357  -0.1239   0.6400   1.0000
   4.500   1.0142   0.02464   0.01401  -0.1230   0.6264   1.0000
   4.750   1.0389   0.02501   0.01445  -0.1222   0.6131   1.0000
   5.000   1.0639   0.02537   0.01491  -0.1213   0.6000   1.0000
   5.250   1.0893   0.02571   0.01533  -0.1205   0.5869   1.0000
   5.500   1.1149   0.02605   0.01575  -0.1197   0.5736   1.0000
   5.750   1.1397   0.02639   0.01615  -0.1186   0.5582   1.0000
   6.000   1.1632   0.02672   0.01656  -0.1173   0.5396   1.0000
   6.250   1.1864   0.02700   0.01685  -0.1157   0.5187   1.0000
   6.500   1.2073   0.02742   0.01732  -0.1141   0.4968   1.0000
   6.750   1.2263   0.02797   0.01803  -0.1123   0.4751   1.0000
   7.000   1.2461   0.02851   0.01871  -0.1107   0.4551   1.0000
   7.250   1.2643   0.02910   0.01947  -0.1089   0.4340   1.0000
   7.500   1.2806   0.02969   0.02023  -0.1068   0.4098   1.0000
   7.750   1.2946   0.03026   0.02088  -0.1044   0.3808   1.0000
   8.000   1.3063   0.03090   0.02149  -0.1017   0.3483   1.0000
   8.250   1.3160   0.03182   0.02228  -0.0988   0.3149   1.0000
   8.500   1.3248   0.03298   0.02335  -0.0961   0.2843   1.0000
   8.750   1.3313   0.03438   0.02465  -0.0933   0.2549   1.0000
   9.000   1.3344   0.03599   0.02617  -0.0903   0.2260   1.0000
   9.250   1.3356   0.03773   0.02788  -0.0873   0.1992   1.0000
   9.500   1.3363   0.03969   0.02985  -0.0845   0.1750   1.0000
   9.750   1.3352   0.04191   0.03203  -0.0819   0.1540   1.0000
  10.000   1.3322   0.04446   0.03449  -0.0795   0.1368   1.0000
  10.250   1.3282   0.04727   0.03726  -0.0773   0.1217   1.0000
  10.500   1.3233   0.05032   0.04024  -0.0754   0.1097   1.0000
  10.750   1.3210   0.05331   0.04331  -0.0738   0.0988   1.0000
  11.000   1.3203   0.05626   0.04635  -0.0722   0.0906   1.0000
  11.250   1.3192   0.05927   0.04938  -0.0710   0.0843   1.0000
  11.500   1.3212   0.06212   0.05240  -0.0698   0.0780   1.0000
  11.750   1.3221   0.06506   0.05548  -0.0688   0.0730   1.0000
  12.000   1.3246   0.06790   0.05837  -0.0677   0.0694   1.0000
  12.250   1.3290   0.07075   0.06152  -0.0666   0.0653   1.0000
  12.500   1.3300   0.07385   0.06474  -0.0660   0.0620   1.0000
  12.750   1.3312   0.07686   0.06774  -0.0655   0.0594   1.0000
  13.000   1.3333   0.08033   0.07158  -0.0648   0.0569   1.0000
  13.250   1.3332   0.08406   0.07558  -0.0644   0.0549   1.0000
  13.500   1.3302   0.08807   0.07980  -0.0645   0.0532   1.0000
  13.750   1.3267   0.09206   0.08393  -0.0649   0.0516   1.0000
  14.000   1.3270   0.09540   0.08730  -0.0650   0.0500   1.0000
  14.250   1.3152   0.10117   0.09337  -0.0666   0.0492   1.0000
  14.500   1.3002   0.10773   0.10025  -0.0692   0.0487   1.0000
  14.750   1.2830   0.11505   0.10785  -0.0726   0.0484   1.0000
  15.000   1.2636   0.12328   0.11631  -0.0770   0.0483   1.0000
  15.250   1.2419   0.13268   0.12594  -0.0825   0.0485   1.0000
  15.500   1.2183   0.14350   0.13695  -0.0894   0.0488   1.0000
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