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GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 195 AIRFOIL (goe195-il)
Reynolds number: 50,000
Max Cl/Cd: 40.68 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe195-il-50000.txt
Download as CSV file: xf-goe195-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3138   0.10699   0.09995  -0.0247   1.0000   0.1979
  -7.750  -0.3173   0.10569   0.09874  -0.0240   1.0000   0.2049
  -7.500  -0.3424   0.10729   0.10056  -0.0229   1.0000   0.2072
  -7.250  -0.3139   0.10052   0.09374  -0.0218   1.0000   0.2149
  -7.000  -0.3270   0.10015   0.09351  -0.0200   1.0000   0.2207
  -6.750  -0.3421   0.09985   0.09340  -0.0201   1.0000   0.2235
  -6.500  -0.3250   0.09494   0.08846  -0.0171   1.0000   0.2299
  -6.250  -0.3359   0.09451   0.08817  -0.0171   1.0000   0.2368
  -6.000  -0.3367   0.09185   0.08560  -0.0162   1.0000   0.2405
  -5.750  -0.3311   0.08895   0.08274  -0.0138   1.0000   0.2473
  -5.500  -0.3409   0.08876   0.08268  -0.0172   1.0000   0.2545
  -5.250  -0.3329   0.08473   0.07869  -0.0126   1.0000   0.2597
  -5.000  -0.3351   0.08406   0.07809  -0.0167   1.0000   0.2699
  -4.750  -0.3297   0.08036   0.07445  -0.0115   1.0000   0.2763
  -4.500  -0.3266   0.07845   0.07260  -0.0137   1.0000   0.2868
  -4.250  -0.3180   0.07681   0.07098  -0.0169   1.0000   0.3003
  -4.000  -0.3147   0.07338   0.06762  -0.0122   1.0000   0.3055
  -3.750  -0.3040   0.07104   0.06529  -0.0147   1.0000   0.3176
  -3.500  -0.2901   0.06873   0.06297  -0.0173   1.0000   0.3315
  -3.250  -0.2789   0.06623   0.06049  -0.0170   1.0000   0.3438
  -3.000  -0.2675   0.06340   0.05770  -0.0166   1.0000   0.3526
  -2.750  -0.0982   0.04627   0.03897  -0.0712   1.0000   0.1776
  -2.500  -0.0574   0.04175   0.03413  -0.0769   1.0000   0.1650
  -2.250  -0.0115   0.03765   0.02948  -0.0832   1.0000   0.1559
  -2.000   0.0364   0.03385   0.02486  -0.0893   1.0000   0.1508
  -1.750   0.0704   0.03207   0.02263  -0.0918   1.0000   0.1515
  -1.500   0.0980   0.03124   0.02156  -0.0930   1.0000   0.1570
  -1.250   0.1269   0.03049   0.02048  -0.0944   1.0000   0.1640
  -1.000   0.1511   0.03029   0.02022  -0.0951   1.0000   0.1720
  -0.750   0.1764   0.03019   0.02001  -0.0960   1.0000   0.1828
  -0.500   0.2200   0.03026   0.02004  -0.0997   0.9944   0.2141
  -0.250   0.2760   0.02993   0.02023  -0.1049   0.9842   0.4072
   0.000   0.3199   0.03062   0.02130  -0.1083   0.9709   0.5222
   0.250   0.3605   0.03087   0.02173  -0.1111   0.9576   0.6039
   0.500   0.4017   0.03083   0.02180  -0.1142   0.9444   0.6675
   0.750   0.4361   0.03022   0.02175  -0.1157   0.9320   0.7740
   1.000   0.4777   0.03082   0.02202  -0.1200   0.9164   1.0000
   1.250   0.5172   0.03168   0.02245  -0.1232   0.9031   1.0000
   1.500   0.5535   0.03249   0.02299  -0.1256   0.8904   1.0000
   1.750   0.5918   0.03322   0.02352  -0.1280   0.8786   1.0000
   2.000   0.6298   0.03387   0.02404  -0.1302   0.8668   1.0000
   2.250   0.6568   0.03471   0.02480  -0.1307   0.8535   1.0000
   2.500   0.6848   0.03553   0.02556  -0.1312   0.8405   1.0000
   2.750   0.7143   0.03628   0.02628  -0.1319   0.8276   1.0000
   3.000   0.7462   0.03692   0.02689  -0.1327   0.8148   1.0000
   3.250   0.7823   0.03732   0.02732  -0.1337   0.8022   1.0000
   3.500   0.8254   0.03730   0.02734  -0.1353   0.7902   1.0000
   3.750   0.8534   0.03785   0.02794  -0.1351   0.7759   1.0000
   4.000   0.8811   0.03840   0.02856  -0.1347   0.7616   1.0000
   4.250   0.9085   0.03891   0.02916  -0.1342   0.7472   1.0000
   4.500   0.9362   0.03940   0.02973  -0.1336   0.7327   1.0000
   4.750   0.9641   0.03984   0.03030  -0.1328   0.7181   1.0000
   5.000   0.9930   0.04013   0.03072  -0.1320   0.7030   1.0000
   5.250   1.0220   0.04038   0.03110  -0.1310   0.6877   1.0000
   5.500   1.0521   0.04042   0.03129  -0.1299   0.6716   1.0000
   5.750   1.0849   0.04004   0.03109  -0.1285   0.6546   1.0000
   6.000   1.1321   0.03779   0.02899  -0.1270   0.6355   1.0000
   6.250   1.1574   0.03729   0.02864  -0.1242   0.6115   1.0000
   6.500   1.1998   0.03534   0.02676  -0.1224   0.5898   1.0000
   6.750   1.2228   0.03545   0.02702  -0.1201   0.5660   1.0000
   7.000   1.2604   0.03441   0.02601  -0.1185   0.5426   1.0000
   7.250   1.2829   0.03450   0.02618  -0.1159   0.5135   1.0000
   7.500   1.3088   0.03385   0.02546  -0.1131   0.4797   1.0000
   7.750   1.3236   0.03377   0.02545  -0.1096   0.4436   1.0000
   8.000   1.3387   0.03334   0.02505  -0.1059   0.4059   1.0000
   8.250   1.3485   0.03315   0.02476  -0.1019   0.3647   1.0000
   8.500   1.3556   0.03370   0.02506  -0.0978   0.3201   1.0000
   8.750   1.3579   0.03520   0.02615  -0.0935   0.2713   1.0000
   9.000   1.3567   0.03767   0.02807  -0.0891   0.2215   1.0000
   9.250   1.3596   0.04053   0.03059  -0.0855   0.1819   1.0000
   9.500   1.3707   0.04315   0.03310  -0.0830   0.1574   1.0000
   9.750   1.3924   0.04586   0.03571  -0.0818   0.1410   1.0000
  10.000   1.4135   0.04876   0.03869  -0.0807   0.1292   1.0000
  10.250   1.4364   0.05205   0.04204  -0.0800   0.1207   1.0000
  10.500   1.4507   0.05543   0.04579  -0.0782   0.1153   1.0000
  10.750   1.4719   0.05926   0.04961  -0.0778   0.1094   1.0000
  11.000   1.4674   0.06277   0.05371  -0.0744   0.1072   1.0000
  11.250   1.4612   0.06664   0.05806  -0.0712   0.1055   1.0000
  11.500   1.4506   0.07075   0.06258  -0.0681   0.1048   1.0000
  11.750   1.4328   0.07478   0.06696  -0.0647   0.1047   1.0000
  12.000   1.4104   0.07913   0.07163  -0.0618   0.1049   1.0000
  12.250   1.3843   0.08402   0.07680  -0.0600   0.1054   1.0000
  12.500   1.3556   0.08963   0.08266  -0.0594   0.1062   1.0000
  12.750   1.3254   0.09608   0.08933  -0.0603   0.1071   1.0000
  13.000   1.2954   0.10342   0.09681  -0.0626   0.1081   1.0000
  13.250   1.2685   0.11142   0.10492  -0.0657   0.1091   1.0000
  13.500   1.2470   0.11971   0.11331  -0.0692   0.1100   1.0000
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