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GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il)
Reynolds number: 200,000
Max Cl/Cd: 80.78 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe167-il-200000.txt
Download as CSV file: xf-goe167-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 167 (V.KARMAN PROP.2) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3776   0.10842   0.10511  -0.0209   1.0000   0.0354
  -8.750  -0.3763   0.10538   0.10212  -0.0247   1.0000   0.0355
  -8.500  -0.3753   0.10208   0.09886  -0.0288   1.0000   0.0356
  -8.250  -0.3675   0.09595   0.09276  -0.0260   1.0000   0.0362
  -8.000  -0.3558   0.09233   0.08914  -0.0243   1.0000   0.0370
  -7.750  -0.3494   0.08924   0.08609  -0.0247   1.0000   0.0377
  -7.500  -0.3439   0.08615   0.08304  -0.0261   1.0000   0.0386
  -7.250  -0.3368   0.08283   0.07976  -0.0287   1.0000   0.0396
  -7.000  -0.3293   0.07945   0.07643  -0.0319   1.0000   0.0412
  -6.750  -0.3228   0.07612   0.07313  -0.0357   1.0000   0.0432
  -6.500  -0.2797   0.07078   0.06746  -0.0548   0.9895   0.0454
  -6.250  -0.2610   0.06344   0.06019  -0.0579   0.9770   0.0466
  -6.000  -0.2354   0.05980   0.05656  -0.0601   0.9587   0.0480
  -5.750  -0.2097   0.05631   0.05297  -0.0633   0.9294   0.0502
  -5.500  -0.1864   0.05288   0.04934  -0.0660   0.8897   0.0537
  -5.250  -0.1556   0.04819   0.04402  -0.0712   0.8531   0.0585
  -5.000  -0.1420   0.04541   0.04115  -0.0699   0.8172   0.0598
  -4.750  -0.1233   0.04324   0.03877  -0.0697   0.7871   0.0620
  -4.500  -0.0867   0.04321   0.03789  -0.0716   0.7624   0.0706
  -4.250  -0.0680   0.03786   0.03248  -0.0727   0.7432   0.0725
  -4.000  -0.0464   0.03575   0.03032  -0.0730   0.7249   0.0755
  -3.750  -0.0142   0.03440   0.02832  -0.0742   0.7100   0.0859
  -3.500   0.0089   0.03170   0.02562  -0.0747   0.6973   0.0886
  -3.250   0.0402   0.03103   0.02437  -0.0753   0.6862   0.1000
  -3.000   0.0648   0.02828   0.02168  -0.0761   0.6760   0.1036
  -2.750   0.0940   0.02699   0.02003  -0.0767   0.6677   0.1159
  -2.500   0.1219   0.02566   0.01852  -0.0774   0.6592   0.1305
  -2.250   0.1492   0.02429   0.01702  -0.0780   0.6520   0.1465
  -2.000   0.1768   0.02303   0.01569  -0.0785   0.6446   0.1644
  -1.750   0.2049   0.02209   0.01453  -0.0790   0.6388   0.1915
  -1.500   0.2511   0.01971   0.01088  -0.0769   0.6333   0.0714
  -1.250   0.2803   0.01875   0.00978  -0.0770   0.6279   0.0699
  -1.000   0.3094   0.01802   0.00888  -0.0771   0.6233   0.0699
  -0.750   0.3386   0.01711   0.00791  -0.0772   0.6179   0.0687
  -0.500   0.3675   0.01649   0.00720  -0.0773   0.6130   0.0681
  -0.250   0.3961   0.01605   0.00668  -0.0773   0.6089   0.0683
   0.000   0.4250   0.01565   0.00631  -0.0775   0.6042   0.0692
   0.250   0.4538   0.01538   0.00603  -0.0777   0.5999   0.0705
   0.500   0.4824   0.01505   0.00572  -0.0779   0.5959   0.0753
   0.750   0.5113   0.01496   0.00564  -0.0782   0.5913   0.0815
   1.000   0.5404   0.01482   0.00551  -0.0784   0.5860   0.0902
   1.250   0.5625   0.01239   0.00536  -0.0772   0.5816   1.0000
   1.500   0.5913   0.01261   0.00533  -0.0773   0.5772   1.0000
   1.750   0.6201   0.01278   0.00544  -0.0775   0.5726   1.0000
   2.000   0.6488   0.01299   0.00557  -0.0778   0.5689   1.0000
   2.250   0.6773   0.01323   0.00569  -0.0780   0.5655   1.0000
   2.500   0.7058   0.01345   0.00589  -0.0782   0.5613   1.0000
   2.750   0.7342   0.01363   0.00608  -0.0784   0.5562   1.0000
   3.000   0.7626   0.01384   0.00623  -0.0786   0.5521   1.0000
   3.250   0.7908   0.01407   0.00640  -0.0787   0.5473   1.0000
   3.500   0.8187   0.01419   0.00658  -0.0789   0.5407   1.0000
   3.750   0.8467   0.01434   0.00664  -0.0789   0.5349   1.0000
   4.000   0.8744   0.01448   0.00683  -0.0790   0.5278   1.0000
   4.250   0.9023   0.01458   0.00690  -0.0790   0.5212   1.0000
   4.500   0.9300   0.01474   0.00709  -0.0790   0.5150   1.0000
   4.750   0.9577   0.01488   0.00730  -0.0791   0.5092   1.0000
   5.000   0.9856   0.01504   0.00742  -0.0791   0.5040   1.0000
   5.250   1.0129   0.01516   0.00768  -0.0792   0.4968   1.0000
   5.500   1.0404   0.01524   0.00775  -0.0791   0.4900   1.0000
   5.750   1.0674   0.01530   0.00792  -0.0791   0.4813   1.0000
   6.000   1.0947   0.01533   0.00795  -0.0790   0.4735   1.0000
   6.250   1.1215   0.01539   0.00818  -0.0789   0.4644   1.0000
   6.500   1.1481   0.01538   0.00824  -0.0787   0.4537   1.0000
   6.750   1.1743   0.01531   0.00824  -0.0784   0.4393   1.0000
   7.000   1.2002   0.01526   0.00830  -0.0781   0.4205   1.0000
   7.250   1.2256   0.01530   0.00838  -0.0777   0.3978   1.0000
   7.500   1.2505   0.01548   0.00858  -0.0774   0.3689   1.0000
   7.750   1.2722   0.01596   0.00887  -0.0766   0.3162   1.0000
   8.000   1.2876   0.01723   0.00972  -0.0753   0.2529   1.0000
   8.250   1.3044   0.01841   0.01072  -0.0742   0.2171   1.0000
   8.500   1.3212   0.01954   0.01171  -0.0730   0.1734   1.0000
   8.750   1.3222   0.02208   0.01357  -0.0702   0.0870   1.0000
   9.000   1.3310   0.02372   0.01517  -0.0680   0.0708   1.0000
   9.250   1.3378   0.02534   0.01684  -0.0655   0.0575   1.0000
   9.500   1.3404   0.02707   0.01867  -0.0625   0.0466   1.0000
   9.750   1.3456   0.02834   0.02005  -0.0597   0.0401   1.0000
  10.000   1.3415   0.03041   0.02214  -0.0565   0.0369   1.0000
  10.250   1.3449   0.03221   0.02409  -0.0546   0.0344   1.0000
  10.500   1.3483   0.03421   0.02618  -0.0532   0.0321   1.0000
  10.750   1.3496   0.03661   0.02863  -0.0522   0.0302   1.0000
  11.000   1.3454   0.03975   0.03184  -0.0514   0.0290   1.0000
  11.250   1.3460   0.04252   0.03474  -0.0507   0.0281   1.0000
  11.500   1.3461   0.04538   0.03773  -0.0500   0.0273   1.0000
  11.750   1.3464   0.04820   0.04064  -0.0494   0.0266   1.0000
  12.000   1.3475   0.05092   0.04345  -0.0486   0.0259   1.0000
  12.250   1.3493   0.05353   0.04613  -0.0478   0.0253   1.0000
  12.500   1.3520   0.05601   0.04868  -0.0468   0.0248   1.0000
  12.750   1.3557   0.05835   0.05108  -0.0456   0.0243   1.0000
  13.000   1.3605   0.06053   0.05329  -0.0441   0.0237   1.0000
  13.250   1.3698   0.06229   0.05510  -0.0414   0.0230   1.0000
  13.500   1.3752   0.06474   0.05775  -0.0406   0.0225   1.0000
  13.750   1.3804   0.06728   0.06047  -0.0397   0.0221   1.0000
  14.000   1.3859   0.06995   0.06334  -0.0385   0.0218   1.0000
  14.250   1.3893   0.07305   0.06665  -0.0375   0.0217   1.0000
  14.500   1.3888   0.07669   0.07054  -0.0369   0.0217   1.0000
  14.750   1.3843   0.08087   0.07496  -0.0367   0.0217   1.0000
  15.000   1.3762   0.08556   0.07991  -0.0370   0.0218   1.0000
  15.250   1.3652   0.09071   0.08530  -0.0378   0.0219   1.0000
  15.500   1.3520   0.09624   0.09107  -0.0390   0.0220   1.0000
  15.750   1.3371   0.10218   0.09724  -0.0408   0.0222   1.0000
  16.000   1.3213   0.10848   0.10374  -0.0431   0.0224   1.0000
  16.250   1.3048   0.11509   0.11055  -0.0459   0.0225   1.0000
  16.500   1.2879   0.12205   0.11769  -0.0491   0.0227   1.0000
  16.750   1.2721   0.12919   0.12499  -0.0524   0.0229   1.0000
  17.000   1.2600   0.13583   0.13180  -0.0562   0.0232   1.0000
  17.250   1.2405   0.14469   0.14091  -0.0625   0.0236   1.0000
  17.500   1.1028   0.20007   0.19675  -0.0988   0.0313   1.0000
  17.750   1.1153   0.19919   0.19590  -0.0982   0.0302   1.0000
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