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GOE 622 AIRFOIL (goe622-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 622 AIRFOIL (goe622-il)
Reynolds number: 200,000
Max Cl/Cd: 64.94 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe622-il-200000-n5.txt
Download as CSV file: xf-goe622-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 622 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5003   0.08509   0.08169  -0.0184   1.0000   0.0119
  -8.250  -0.5026   0.08049   0.07714  -0.0212   1.0000   0.0120
  -8.000  -0.5062   0.07555   0.07226  -0.0250   1.0000   0.0121
  -7.750  -0.5057   0.06948   0.06621  -0.0311   1.0000   0.0122
  -7.500  -0.5039   0.06264   0.05934  -0.0371   1.0000   0.0122
  -7.000  -0.5005   0.04637   0.04278  -0.0456   1.0000   0.0121
  -6.750  -0.5006   0.03637   0.03223  -0.0471   1.0000   0.0121
  -6.500  -0.4927   0.03018   0.02538  -0.0466   1.0000   0.0122
  -6.250  -0.4789   0.02621   0.02082  -0.0455   1.0000   0.0125
  -6.000  -0.4618   0.02339   0.01745  -0.0442   1.0000   0.0130
  -5.750  -0.4425   0.02125   0.01488  -0.0430   1.0000   0.0136
  -5.500  -0.4109   0.01949   0.01273  -0.0441   0.9971   0.0146
  -5.250  -0.3764   0.01741   0.01033  -0.0460   0.9930   0.0171
  -5.000  -0.3427   0.01628   0.00902  -0.0474   0.9888   0.0193
  -4.750  -0.3093   0.01532   0.00788  -0.0486   0.9848   0.0226
  -4.500  -0.2765   0.01451   0.00694  -0.0498   0.9801   0.0276
  -4.250  -0.2423   0.01389   0.00620  -0.0513   0.9762   0.0352
  -4.000  -0.2104   0.01334   0.00561  -0.0523   0.9702   0.0460
  -3.750  -0.1761   0.01283   0.00509  -0.0538   0.9660   0.0601
  -3.500  -0.1452   0.01246   0.00478  -0.0545   0.9589   0.0768
  -3.250  -0.1111   0.01214   0.00443  -0.0559   0.9537   0.0928
  -3.000  -0.0800   0.01187   0.00412  -0.0566   0.9461   0.1080
  -2.750  -0.0464   0.01159   0.00382  -0.0578   0.9401   0.1254
  -2.500  -0.0153   0.01133   0.00355  -0.0585   0.9321   0.1405
  -2.250   0.0177   0.01105   0.00330  -0.0596   0.9255   0.1588
  -2.000   0.0476   0.01075   0.00309  -0.0601   0.9164   0.1907
  -1.750   0.0778   0.01032   0.00291  -0.0607   0.9081   0.2600
  -1.500   0.1061   0.00981   0.00278  -0.0610   0.8987   0.3724
  -1.250   0.1319   0.00923   0.00269  -0.0606   0.8884   0.5202
  -1.000   0.1550   0.00863   0.00266  -0.0593   0.8778   0.6858
  -0.750   0.1782   0.00825   0.00267  -0.0573   0.8673   0.8375
  -0.500   0.2181   0.00812   0.00261  -0.0592   0.8569   0.9454
  -0.250   0.2609   0.00808   0.00249  -0.0623   0.8452   0.9983
   0.000   0.2878   0.00812   0.00242  -0.0619   0.8311   1.0000
   0.250   0.3136   0.00816   0.00236  -0.0613   0.8152   1.0000
   0.500   0.3388   0.00820   0.00228  -0.0605   0.7913   1.0000
   0.750   0.3636   0.00827   0.00219  -0.0595   0.7594   1.0000
   1.000   0.3884   0.00837   0.00211  -0.0586   0.7243   1.0000
   1.250   0.4136   0.00850   0.00208  -0.0579   0.6939   1.0000
   1.500   0.4390   0.00866   0.00208  -0.0572   0.6671   1.0000
   1.750   0.4648   0.00882   0.00214  -0.0567   0.6450   1.0000
   2.250   0.5165   0.00917   0.00230  -0.0557   0.6062   1.0000
   2.500   0.5423   0.00937   0.00243  -0.0552   0.5860   1.0000
   2.750   0.5682   0.00957   0.00256  -0.0548   0.5683   1.0000
   3.000   0.5943   0.00976   0.00271  -0.0544   0.5503   1.0000
   3.250   0.6201   0.00997   0.00290  -0.0540   0.5294   1.0000
   3.500   0.6458   0.01020   0.00307  -0.0536   0.5067   1.0000
   3.750   0.6711   0.01045   0.00326  -0.0531   0.4775   1.0000
   4.000   0.6959   0.01074   0.00346  -0.0525   0.4407   1.0000
   4.250   0.7202   0.01109   0.00370  -0.0519   0.3960   1.0000
   4.750   0.7666   0.01212   0.00433  -0.0505   0.2983   1.0000
   5.000   0.7883   0.01287   0.00477  -0.0497   0.2371   1.0000
   5.250   0.8112   0.01351   0.00523  -0.0491   0.1892   1.0000
   5.500   0.8338   0.01420   0.00570  -0.0485   0.1432   1.0000
   5.750   0.8566   0.01487   0.00623  -0.0479   0.1155   1.0000
   6.000   0.8801   0.01546   0.00677  -0.0473   0.0864   1.0000
   6.250   0.8995   0.01663   0.00759  -0.0463   0.0291   1.0000
   6.500   0.9209   0.01755   0.00850  -0.0453   0.0192   1.0000
   6.750   0.9436   0.01830   0.00939  -0.0444   0.0169   1.0000
   7.000   0.9652   0.01917   0.01040  -0.0434   0.0150   1.0000
   7.250   0.9849   0.02031   0.01172  -0.0422   0.0128   1.0000
   7.500   1.0016   0.02181   0.01344  -0.0405   0.0117   1.0000
   7.750   1.0197   0.02306   0.01482  -0.0391   0.0113   1.0000
   8.000   1.0376   0.02435   0.01626  -0.0377   0.0109   1.0000
   8.250   1.0550   0.02578   0.01784  -0.0362   0.0105   1.0000
   8.500   1.0726   0.02718   0.01945  -0.0348   0.0099   1.0000
   8.750   1.0900   0.02854   0.02095  -0.0336   0.0091   1.0000
   9.000   1.1062   0.03001   0.02256  -0.0322   0.0085   1.0000
   9.250   1.1209   0.03181   0.02452  -0.0307   0.0082   1.0000
   9.500   1.1341   0.03380   0.02669  -0.0291   0.0079   1.0000
   9.750   1.1452   0.03604   0.02913  -0.0274   0.0077   1.0000
  10.000   1.1538   0.03861   0.03191  -0.0255   0.0076   1.0000
  10.250   1.1586   0.04152   0.03507  -0.0234   0.0074   1.0000
  10.500   1.1581   0.04456   0.03839  -0.0208   0.0074   1.0000
  10.750   1.1530   0.04762   0.04172  -0.0180   0.0073   1.0000
  11.000   1.1445   0.05085   0.04521  -0.0155   0.0073   1.0000
  11.500   1.1223   0.05796   0.05280  -0.0130   0.0073   1.0000
  11.750   1.1094   0.06212   0.05719  -0.0130   0.0073   1.0000
  12.750   1.0529   0.08395   0.07985  -0.0232   0.0073   1.0000
  13.000   1.0384   0.09088   0.08696  -0.0278   0.0074   1.0000
  13.250   1.0228   0.09870   0.09495  -0.0331   0.0074   1.0000
  13.500   1.0062   0.10769   0.10410  -0.0392   0.0075   1.0000
  13.750   0.9837   0.11961   0.11620  -0.0471   0.0077   1.0000
  14.000   0.9321   0.14342   0.14017  -0.0596   0.0084   1.0000
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