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GOE 12K AIRFOIL (goe12k-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 12K AIRFOIL (goe12k-il)
Reynolds number: 50,000
Max Cl/Cd: 28.92 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe12k-il-50000.txt
Download as CSV file: xf-goe12k-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 12K 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.5402   0.11338   0.10692  -0.0083   1.0000   0.2619
  -7.000  -0.5153   0.10862   0.10212  -0.0065   1.0000   0.2742
  -6.750  -0.5612   0.10848   0.10214  -0.0035   1.0000   0.2786
  -6.500  -0.5467   0.10462   0.09828  -0.0010   1.0000   0.2933
  -6.250  -0.4409   0.09727   0.09133  -0.0010   1.0000   0.3254
  -6.000  -0.4431   0.09428   0.08838   0.0013   1.0000   0.3383
  -5.750  -0.5923   0.09795   0.09178   0.0049   1.0000   0.3297
  -5.500  -0.5750   0.09402   0.08786   0.0093   1.0000   0.3499
  -5.250  -0.5732   0.09127   0.08514   0.0124   1.0000   0.3684
  -5.000  -0.5730   0.08875   0.08264   0.0159   1.0000   0.3911
  -4.750  -0.5758   0.08619   0.08013   0.0199   1.0000   0.4189
  -4.500  -0.5699   0.08386   0.07783   0.0251   1.0000   0.4557
  -4.000  -0.0817   0.06811   0.06078  -0.0237   1.0000   1.0000
  -3.750  -0.1215   0.06767   0.06053  -0.0119   1.0000   0.9814
  -3.500  -0.1796   0.06766   0.06073   0.0028   1.0000   0.9461
  -3.250  -0.2454   0.06756   0.06086   0.0171   1.0000   0.9002
  -3.000  -0.3176   0.06673   0.06025   0.0297   1.0000   0.8390
  -2.750  -0.4823   0.05155   0.04305  -0.0071   1.0000   0.2430
  -2.500  -0.4575   0.04792   0.03847  -0.0074   1.0000   0.2116
  -2.250  -0.4400   0.04561   0.03598  -0.0061   1.0000   0.2075
  -2.000  -0.4217   0.04372   0.03374  -0.0047   1.0000   0.2060
  -1.750  -0.4023   0.04197   0.03155  -0.0033   1.0000   0.2024
  -1.500  -0.3817   0.04045   0.02952  -0.0019   1.0000   0.1985
  -1.250  -0.3609   0.03929   0.02791  -0.0004   1.0000   0.1971
  -1.000  -0.3412   0.03817   0.02669   0.0007   1.0000   0.2001
  -0.750  -0.3204   0.03731   0.02565   0.0019   1.0000   0.2040
  -0.500  -0.2974   0.03653   0.02459   0.0027   1.0000   0.2061
  -0.250  -0.2735   0.03587   0.02367   0.0034   1.0000   0.2085
   0.000  -0.2491   0.03538   0.02292   0.0039   1.0000   0.2120
   0.250  -0.2196   0.03488   0.02243   0.0032   1.0000   0.2203
   0.500  -0.1856   0.03474   0.02216   0.0016   1.0000   0.2323
   0.750  -0.1525   0.03468   0.02203   0.0002   1.0000   0.2461
   1.000  -0.1194   0.03457   0.02206  -0.0012   1.0000   0.2680
   1.250  -0.0827   0.03427   0.02238  -0.0034   1.0000   0.3453
   1.500   0.0207   0.03490   0.02413  -0.0185   1.0000   1.0000
   1.750   0.0404   0.03546   0.02448  -0.0177   1.0000   1.0000
   2.000   0.0600   0.03605   0.02491  -0.0169   1.0000   1.0000
   2.250   0.0792   0.03667   0.02540  -0.0161   1.0000   1.0000
   2.500   0.0983   0.03733   0.02595  -0.0154   1.0000   1.0000
   2.750   0.1172   0.03803   0.02657  -0.0148   1.0000   1.0000
   3.000   0.1356   0.03877   0.02725  -0.0141   1.0000   1.0000
   3.250   0.1536   0.03957   0.02800  -0.0135   1.0000   1.0000
   3.500   0.1712   0.04042   0.02882  -0.0129   1.0000   1.0000
   3.750   0.1882   0.04134   0.02974  -0.0123   1.0000   1.0000
   4.000   0.2046   0.04236   0.03076  -0.0118   1.0000   1.0000
   4.250   0.2200   0.04348   0.03191  -0.0113   1.0000   1.0000
   4.500   0.2343   0.04473   0.03320  -0.0110   1.0000   1.0000
   4.750   0.2473   0.04612   0.03464  -0.0107   1.0000   1.0000
   5.000   0.2592   0.04769   0.03626  -0.0105   1.0000   1.0000
   5.250   0.3020   0.05101   0.03971  -0.0167   0.9853   1.0000
   5.500   0.4130   0.05314   0.04207  -0.0326   0.9030   1.0000
   5.750   0.4596   0.05422   0.04330  -0.0367   0.8716   1.0000
   6.000   0.4984   0.05494   0.04415  -0.0393   0.8431   1.0000
   6.250   0.5387   0.05539   0.04477  -0.0416   0.8165   1.0000
   6.500   0.5864   0.05538   0.04496  -0.0443   0.7907   1.0000
   6.750   0.6444   0.05418   0.04403  -0.0472   0.7632   1.0000
   7.000   0.6976   0.05121   0.04133  -0.0474   0.7271   1.0000
   7.250   0.7630   0.04650   0.03700  -0.0474   0.6928   1.0000
   7.500   0.8122   0.04254   0.03339  -0.0457   0.6606   1.0000
   7.750   0.8493   0.03872   0.02993  -0.0419   0.6201   1.0000
   8.000   0.9308   0.03219   0.02182  -0.0380   0.3888   1.0000
   8.250   0.9389   0.03421   0.02300  -0.0343   0.3045   1.0000
   8.500   0.9772   0.03572   0.02402  -0.0353   0.2549   1.0000
   8.750   1.0682   0.03802   0.02586  -0.0451   0.2126   1.0000
   9.000   1.1241   0.04068   0.02872  -0.0499   0.1913   1.0000
   9.250   1.1742   0.04379   0.03202  -0.0541   0.1756   1.0000
   9.500   1.2087   0.04681   0.03523  -0.0556   0.1642   1.0000
   9.750   1.2310   0.04952   0.03822  -0.0548   0.1562   1.0000
  10.000   1.2472   0.05270   0.04166  -0.0532   0.1500   1.0000
  10.250   1.2468   0.05541   0.04485  -0.0485   0.1468   1.0000
  10.500   1.2479   0.05818   0.04796  -0.0445   0.1435   1.0000
  10.750   1.2742   0.06238   0.05210  -0.0453   0.1372   1.0000
  11.000   1.2620   0.06522   0.05537  -0.0394   0.1366   1.0000
  11.250   1.2470   0.06827   0.05878  -0.0335   0.1363   1.0000
  11.500   1.2282   0.07121   0.06200  -0.0274   0.1362   1.0000
  11.750   1.2078   0.07435   0.06541  -0.0216   0.1363   1.0000
  12.000   1.1865   0.07779   0.06909  -0.0164   0.1366   1.0000
  12.250   1.1621   0.08142   0.07293  -0.0117   0.1368   1.0000
  12.500   1.1425   0.08568   0.07737  -0.0082   0.1372   1.0000
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