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GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il)
Reynolds number: 200,000
Max Cl/Cd: 83.07 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe610bm-il-200000.txt
Download as CSV file: xf-goe610bm-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610-B MOD. AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.2980   0.09192   0.08880  -0.0251   1.0000   0.0293
  -6.750  -0.3083   0.09073   0.08769  -0.0228   1.0000   0.0296
  -6.500  -0.3204   0.08975   0.08679  -0.0203   1.0000   0.0300
  -6.250  -0.3085   0.08688   0.08395  -0.0250   0.9971   0.0311
  -6.000  -0.2526   0.08194   0.07891  -0.0449   0.9895   0.0324
  -5.750  -0.2061   0.07645   0.07332  -0.0577   0.9845   0.0327
  -5.500  -0.1863   0.06909   0.06597  -0.0621   0.9800   0.0335
  -5.250  -0.1691   0.06566   0.06255  -0.0615   0.9753   0.0353
  -5.000  -0.1317   0.06137   0.05820  -0.0686   0.9717   0.0380
  -4.750  -0.0831   0.05630   0.05299  -0.0795   0.9677   0.0417
  -4.500  -0.0104   0.05033   0.04658  -0.0965   0.9613   0.0448
  -4.250   0.0103   0.04537   0.04171  -0.0984   0.9570   0.0470
  -4.000   0.0410   0.04259   0.03886  -0.1014   0.9496   0.0510
  -3.750   0.0937   0.03744   0.03326  -0.1101   0.9437   0.0600
  -3.500   0.1189   0.03524   0.03108  -0.1111   0.9349   0.0636
  -3.250   0.1608   0.03173   0.02711  -0.1155   0.9278   0.0745
  -3.000   0.1843   0.03001   0.02542  -0.1156   0.9173   0.0798
  -2.750   0.2138   0.02800   0.02318  -0.1167   0.9079   0.0932
  -2.500   0.2427   0.02616   0.02111  -0.1174   0.8987   0.1069
  -2.250   0.2699   0.02470   0.01951  -0.1177   0.8876   0.1225
  -2.000   0.2973   0.02353   0.01815  -0.1180   0.8769   0.1475
  -1.500   0.3719   0.01773   0.01072  -0.1178   0.8575   0.0738
  -1.250   0.3999   0.01655   0.00937  -0.1173   0.8457   0.0700
  -1.000   0.4277   0.01569   0.00829  -0.1168   0.8335   0.0701
  -0.750   0.4553   0.01495   0.00738  -0.1162   0.8208   0.0702
  -0.500   0.4829   0.01422   0.00652  -0.1156   0.8076   0.0693
  -0.250   0.5103   0.01365   0.00585  -0.1150   0.7935   0.0694
   0.000   0.5377   0.01321   0.00533  -0.1145   0.7783   0.0704
   0.250   0.5651   0.01289   0.00493  -0.1141   0.7623   0.0719
   0.500   0.5927   0.01253   0.00453  -0.1138   0.7459   0.0758
   0.750   0.6203   0.01240   0.00431  -0.1135   0.7291   0.0835
   1.000   0.6481   0.01230   0.00410  -0.1132   0.7124   0.0928
   1.250   0.6694   0.01024   0.00408  -0.1119   0.6962   1.0000
   1.500   0.6972   0.01041   0.00400  -0.1116   0.6791   1.0000
   1.750   0.7249   0.01058   0.00399  -0.1114   0.6629   1.0000
   2.000   0.7525   0.01075   0.00401  -0.1113   0.6478   1.0000
   2.250   0.7802   0.01093   0.00406  -0.1112   0.6339   1.0000
   2.500   0.8079   0.01112   0.00415  -0.1111   0.6211   1.0000
   2.750   0.8355   0.01132   0.00424  -0.1111   0.6094   1.0000
   3.000   0.8631   0.01155   0.00436  -0.1110   0.5986   1.0000
   3.250   0.8908   0.01177   0.00454  -0.1110   0.5876   1.0000
   3.500   0.9182   0.01201   0.00473  -0.1109   0.5764   1.0000
   3.750   0.9453   0.01226   0.00491  -0.1108   0.5643   1.0000
   4.000   0.9721   0.01253   0.00509  -0.1106   0.5517   1.0000
   4.250   0.9991   0.01283   0.00531  -0.1104   0.5409   1.0000
   4.500   1.0262   0.01308   0.00561  -0.1103   0.5301   1.0000
   4.750   1.0531   0.01337   0.00590  -0.1102   0.5197   1.0000
   5.000   1.0798   0.01366   0.00618  -0.1101   0.5090   1.0000
   5.250   1.1059   0.01392   0.00642  -0.1098   0.4956   1.0000
   5.500   1.1316   0.01411   0.00666  -0.1094   0.4800   1.0000
   5.750   1.1573   0.01430   0.00688  -0.1091   0.4645   1.0000
   6.000   1.1825   0.01444   0.00707  -0.1086   0.4454   1.0000
   6.250   1.2073   0.01463   0.00725  -0.1081   0.4242   1.0000
   6.500   1.2319   0.01483   0.00750  -0.1076   0.3991   1.0000
   6.750   1.2553   0.01514   0.00774  -0.1070   0.3599   1.0000
   7.000   1.2773   0.01569   0.00812  -0.1062   0.3103   1.0000
   7.250   1.2925   0.01710   0.00893  -0.1047   0.2127   1.0000
   7.500   1.3073   0.01866   0.01004  -0.1032   0.1492   1.0000
   7.750   1.3251   0.01981   0.01101  -0.1019   0.1112   1.0000
   8.000   1.3415   0.02105   0.01199  -0.1005   0.0675   1.0000
   8.250   1.3516   0.02287   0.01349  -0.0982   0.0295   1.0000
   8.500   1.3685   0.02390   0.01464  -0.0965   0.0270   1.0000
   8.750   1.3840   0.02500   0.01589  -0.0947   0.0255   1.0000
   9.000   1.3964   0.02630   0.01734  -0.0925   0.0239   1.0000
   9.250   1.4033   0.02789   0.01915  -0.0896   0.0225   1.0000
   9.500   1.4076   0.02943   0.02085  -0.0864   0.0219   1.0000
   9.750   1.4094   0.03102   0.02259  -0.0829   0.0216   1.0000
  10.000   1.4106   0.03286   0.02456  -0.0798   0.0214   1.0000
  10.250   1.4117   0.03489   0.02672  -0.0771   0.0213   1.0000
  10.500   1.4130   0.03707   0.02902  -0.0746   0.0212   1.0000
  10.750   1.4152   0.03933   0.03139  -0.0723   0.0211   1.0000
  11.000   1.4190   0.04162   0.03379  -0.0702   0.0211   1.0000
  11.250   1.4251   0.04388   0.03616  -0.0681   0.0211   1.0000
  11.500   1.4346   0.04612   0.03850  -0.0661   0.0213   1.0000
  11.750   1.4483   0.04845   0.04097  -0.0642   0.0215   1.0000
  12.000   1.4602   0.05092   0.04361  -0.0625   0.0215   1.0000
  12.250   1.4668   0.05351   0.04643  -0.0609   0.0212   1.0000
  12.500   1.4713   0.05641   0.04955  -0.0593   0.0211   1.0000
  12.750   1.4771   0.06008   0.05348  -0.0577   0.0215   1.0000
  13.000   1.4940   0.06378   0.05736  -0.0563   0.0225   1.0000
  13.250   1.4904   0.06598   0.05979  -0.0549   0.0230   1.0000
  13.500   1.4789   0.06974   0.06401  -0.0537   0.0243   1.0000
  13.750   1.4558   0.07576   0.07052  -0.0532   0.0258   1.0000
  14.000   1.4366   0.08175   0.07684  -0.0533   0.0269   1.0000
  14.250   1.4175   0.08789   0.08325  -0.0542   0.0277   1.0000
  14.500   1.3979   0.09429   0.08987  -0.0556   0.0283   1.0000
  14.750   1.3777   0.10112   0.09689  -0.0576   0.0288   1.0000
  15.000   1.3672   0.10705   0.10317  -0.0598   0.0318   1.0000
  15.250   1.3428   0.11499   0.11132  -0.0643   0.0319   1.0000
  15.500   1.3197   0.12335   0.11987  -0.0695   0.0319   1.0000
  15.750   1.2982   0.13211   0.12878  -0.0752   0.0318   1.0000
  16.000   1.2776   0.14141   0.13822  -0.0816   0.0316   1.0000
  16.250   1.2573   0.15149   0.14842  -0.0887   0.0314   1.0000
  16.500   1.2370   0.16248   0.15950  -0.0965   0.0311   1.0000
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