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GOE 598 AIRFOIL (goe598-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 598 AIRFOIL (goe598-il)
Reynolds number: 200,000
Max Cl/Cd: 48.59 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe598-il-200000-n5.txt
Download as CSV file: xf-goe598-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 598 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6205   0.08191   0.07865  -0.0028   1.0000   0.0101
  -8.000  -0.6228   0.07596   0.07274  -0.0087   1.0000   0.0099
  -7.750  -0.6202   0.06905   0.06579  -0.0157   1.0000   0.0098
  -7.500  -0.6160   0.06229   0.05893  -0.0209   1.0000   0.0096
  -7.250  -0.6097   0.05564   0.05210  -0.0247   1.0000   0.0094
  -7.000  -0.6012   0.04909   0.04530  -0.0272   1.0000   0.0092
  -6.750  -0.5903   0.04268   0.03854  -0.0286   1.0000   0.0091
  -6.500  -0.5770   0.03659   0.03198  -0.0290   1.0000   0.0090
  -6.250  -0.5607   0.03139   0.02621  -0.0288   1.0000   0.0090
  -6.000  -0.5413   0.02719   0.02140  -0.0281   1.0000   0.0092
  -5.750  -0.5192   0.02421   0.01788  -0.0274   1.0000   0.0098
  -5.500  -0.4966   0.02144   0.01453  -0.0267   1.0000   0.0111
  -5.250  -0.4732   0.01926   0.01204  -0.0260   1.0000   0.0122
  -5.000  -0.4489   0.01770   0.01024  -0.0253   1.0000   0.0133
  -4.750  -0.4244   0.01638   0.00874  -0.0246   1.0000   0.0150
  -4.500  -0.3994   0.01557   0.00775  -0.0240   1.0000   0.0185
  -4.250  -0.3756   0.01432   0.00640  -0.0232   1.0000   0.0214
  -4.000  -0.3511   0.01361   0.00557  -0.0227   1.0000   0.0281
  -3.750  -0.3269   0.01277   0.00463  -0.0221   1.0000   0.0344
  -3.500  -0.3024   0.01214   0.00396  -0.0216   1.0000   0.0439
  -3.250  -0.2776   0.01168   0.00359  -0.0212   1.0000   0.0611
  -3.000  -0.2525   0.01139   0.00326  -0.0207   1.0000   0.0834
  -2.750  -0.2275   0.01112   0.00294  -0.0203   1.0000   0.0989
  -2.500  -0.2027   0.01083   0.00270  -0.0199   1.0000   0.1201
  -2.250  -0.1780   0.01042   0.00250  -0.0196   1.0000   0.1733
  -2.000  -0.1500   0.00992   0.00230  -0.0202   0.9981   0.2646
  -1.750  -0.1154   0.00933   0.00215  -0.0222   0.9921   0.3859
  -1.500  -0.0809   0.00883   0.00209  -0.0240   0.9858   0.5164
  -1.250  -0.0476   0.00847   0.00202  -0.0253   0.9778   0.6072
  -1.000  -0.0170   0.00809   0.00201  -0.0258   0.9684   0.7026
  -0.750   0.0102   0.00770   0.00208  -0.0250   0.9583   0.8317
  -0.500   0.0550   0.00755   0.00211  -0.0279   0.9535   0.9626
  -0.250   0.0985   0.00751   0.00203  -0.0314   0.9431   1.0000
   0.000   0.1316   0.00750   0.00198  -0.0325   0.9271   1.0000
   0.250   0.1621   0.00749   0.00193  -0.0330   0.9062   1.0000
   0.750   0.2184   0.00752   0.00186  -0.0326   0.8617   1.0000
   1.000   0.2441   0.00758   0.00186  -0.0319   0.8358   1.0000
   1.250   0.2690   0.00768   0.00187  -0.0309   0.8066   1.0000
   1.500   0.2940   0.00781   0.00191  -0.0301   0.7781   1.0000
   1.750   0.3197   0.00794   0.00199  -0.0294   0.7540   1.0000
   2.000   0.3456   0.00807   0.00212  -0.0289   0.7318   1.0000
   2.250   0.3710   0.00823   0.00223  -0.0282   0.7010   1.0000
   2.500   0.3959   0.00844   0.00235  -0.0273   0.6603   1.0000
   2.750   0.4213   0.00867   0.00254  -0.0267   0.6204   1.0000
   3.000   0.4431   0.00926   0.00263  -0.0253   0.4777   1.0000
   3.250   0.4601   0.01105   0.00309  -0.0242   0.1982   1.0000
   3.500   0.4819   0.01238   0.00370  -0.0238   0.0513   1.0000
   3.750   0.5067   0.01321   0.00444  -0.0233   0.0233   1.0000
   4.000   0.5320   0.01390   0.00525  -0.0228   0.0171   1.0000
   4.250   0.5562   0.01491   0.00642  -0.0220   0.0149   1.0000
   4.500   0.5802   0.01594   0.00759  -0.0213   0.0139   1.0000
   4.750   0.6043   0.01705   0.00880  -0.0205   0.0123   1.0000
   5.000   0.6286   0.01816   0.01002  -0.0198   0.0106   1.0000
   5.250   0.6527   0.01969   0.01175  -0.0190   0.0100   1.0000
   5.500   0.6771   0.02148   0.01375  -0.0181   0.0096   1.0000
   5.750   0.7011   0.02359   0.01616  -0.0172   0.0094   1.0000
   6.000   0.7244   0.02607   0.01902  -0.0161   0.0093   1.0000
   6.250   0.7462   0.02903   0.02243  -0.0149   0.0093   1.0000
   6.500   0.7654   0.03190   0.02569  -0.0139   0.0089   1.0000
   6.750   0.7779   0.03642   0.03069  -0.0127   0.0082   1.0000
   7.000   0.7909   0.04057   0.03538  -0.0113   0.0076   1.0000
   7.250   0.8022   0.04479   0.04001  -0.0102   0.0075   1.0000
   7.500   0.8082   0.04963   0.04521  -0.0093   0.0077   1.0000
   8.000   0.8155   0.05839   0.05453  -0.0083   0.0081   1.0000
   8.250   0.8212   0.06218   0.05854  -0.0081   0.0084   1.0000
   8.500   0.8138   0.07179   0.06843  -0.0101   0.0100   1.0000
   8.750   0.8001   0.07809   0.07484  -0.0132   0.0103   1.0000
   9.000   0.7894   0.08593   0.08272  -0.0209   0.0105   1.0000
   9.250   0.7827   0.09357   0.09032  -0.0273   0.0109   1.0000
   9.500   0.7776   0.10004   0.09675  -0.0315   0.0114   1.0000
   9.750   0.7737   0.10595   0.10263  -0.0348   0.0121   1.0000
  10.000   0.7710   0.11139   0.10804  -0.0374   0.0129   1.0000
  10.500   0.6262   0.10869   0.10548  -0.0242   0.0111   1.0000
  10.750   0.6209   0.11371   0.11048  -0.0257   0.0116   1.0000
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