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GOE 780 AIRFOIL (goe780-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 780 AIRFOIL (goe780-il)
Reynolds number: 1,000,000
Max Cl/Cd: 44.04 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe780-il-1000000-n5.txt
Download as CSV file: xf-goe780-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 780 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4074   0.08487   0.08265  -0.0777   0.8372   0.0017
 -10.750  -0.4144   0.07966   0.07740  -0.0805   0.8284   0.0017
 -10.500  -0.4301   0.07240   0.07013  -0.0861   0.8208   0.0016
 -10.250  -0.4391   0.06853   0.06620  -0.0885   0.8147   0.0016
 -10.000  -0.4702   0.06273   0.06032  -0.0885   0.8084   0.0017
  -9.500  -0.5047   0.05679   0.05420  -0.0831   0.7992   0.0016
  -9.250  -0.5117   0.05517   0.05251  -0.0800   0.7953   0.0015
  -9.000  -0.5384   0.05185   0.04905  -0.0731   0.7912   0.0015
  -8.750  -0.5506   0.04877   0.04584  -0.0683   0.7880   0.0015
  -8.500  -0.5602   0.04537   0.04228  -0.0635   0.7850   0.0014
  -8.250  -0.5711   0.04120   0.03789  -0.0578   0.7818   0.0014
  -8.000  -0.5796   0.03666   0.03308  -0.0519   0.7789   0.0013
  -7.750  -0.6191   0.02229   0.01761  -0.0376   0.7761   0.0013
  -7.500  -0.6032   0.01917   0.01403  -0.0354   0.7742   0.0017
  -7.250  -0.5815   0.01660   0.01105  -0.0345   0.7725   0.0015
  -7.000  -0.5578   0.01595   0.01026  -0.0340   0.7705   0.0020
  -6.750  -0.5341   0.01476   0.00887  -0.0335   0.7685   0.0021
  -6.500  -0.5112   0.01375   0.00769  -0.0328   0.7664   0.0021
  -6.250  -0.4894   0.01297   0.00678  -0.0320   0.7643   0.0024
  -6.000  -0.4669   0.01262   0.00640  -0.0313   0.7622   0.0026
  -5.750  -0.4452   0.01212   0.00579  -0.0303   0.7602   0.0030
  -5.500  -0.4238   0.01160   0.00519  -0.0293   0.7585   0.0029
  -5.250  -0.4027   0.01112   0.00463  -0.0281   0.7566   0.0035
  -5.000  -0.3809   0.01076   0.00420  -0.0271   0.7547   0.0038
  -4.750  -0.3599   0.01033   0.00369  -0.0259   0.7526   0.0041
  -4.500  -0.3379   0.01003   0.00336  -0.0250   0.7506   0.0055
  -4.250  -0.3152   0.00980   0.00306  -0.0242   0.7486   0.0064
  -4.000  -0.2933   0.00952   0.00272  -0.0232   0.7467   0.0091
  -3.750  -0.2701   0.00931   0.00249  -0.0224   0.7451   0.0144
  -3.500  -0.2470   0.00910   0.00235  -0.0217   0.7433   0.0299
  -3.250  -0.2231   0.00894   0.00220  -0.0212   0.7414   0.0361
  -3.000  -0.1986   0.00884   0.00207  -0.0208   0.7393   0.0395
  -2.750  -0.1751   0.00867   0.00192  -0.0201   0.7372   0.0482
  -2.500  -0.1506   0.00858   0.00178  -0.0197   0.7354   0.0521
  -2.250  -0.1267   0.00845   0.00167  -0.0191   0.7337   0.0638
  -2.000  -0.1036   0.00827   0.00159  -0.0184   0.7318   0.1005
  -1.750  -0.0789   0.00817   0.00151  -0.0181   0.7300   0.1102
  -1.500  -0.0544   0.00806   0.00143  -0.0176   0.7280   0.1222
  -1.250  -0.0416   0.00734   0.00126  -0.0149   0.7258   0.2932
  -1.000  -0.0265   0.00682   0.00114  -0.0126   0.7237   0.4126
  -0.750  -0.0303   0.00585   0.00096  -0.0060   0.7212   0.6317
  -0.500  -0.0168   0.00558   0.00089  -0.0030   0.7190   0.6945
  -0.250  -0.0057   0.00526   0.00084   0.0006   0.7160   0.7568
   0.000   0.0084   0.00506   0.00093   0.0038   0.7130   0.8343
   0.250   0.0309   0.00505   0.00096   0.0048   0.7087   0.8582
   0.500   0.0551   0.00506   0.00100   0.0055   0.7048   0.8741
   0.750   0.0796   0.00508   0.00104   0.0061   0.7014   0.8849
   1.000   0.1079   0.00508   0.00107   0.0057   0.6976   0.8888
   1.250   0.1358   0.00510   0.00108   0.0054   0.6920   0.8925
   1.500   0.1617   0.00511   0.00112   0.0056   0.6873   0.8958
   1.750   0.1853   0.00512   0.00113   0.0063   0.6805   0.8994
   2.000   0.2100   0.00518   0.00113   0.0068   0.6509   0.9023
   2.250   0.2343   0.00532   0.00119   0.0073   0.6141   0.9053
   2.500   0.2225   0.00663   0.00160   0.0154   0.3808   0.9117
   2.750   0.2135   0.00817   0.00218   0.0223   0.0921   0.9182
   3.000   0.2370   0.00842   0.00235   0.0228   0.0601   0.9213
   3.250   0.2546   0.00874   0.00253   0.0246   0.0148   0.9265
   3.500   0.2820   0.00897   0.00280   0.0243   0.0101   0.9299
   3.750   0.3114   0.00923   0.00313   0.0235   0.0076   0.9331
   4.000   0.3360   0.00949   0.00342   0.0238   0.0061   0.9397
   4.250   0.3602   0.00989   0.00387   0.0241   0.0050   0.9429
   4.500   0.3885   0.01033   0.00439   0.0234   0.0046   0.9449
   4.750   0.4136   0.01089   0.00503   0.0234   0.0041   0.9469
   5.000   0.4378   0.01131   0.00548   0.0236   0.0036   0.9496
   5.250   0.4518   0.01159   0.00576   0.0261   0.0030   0.9552
   5.500   0.4767   0.01237   0.00663   0.0260   0.0028   0.9567
   5.750   0.5012   0.01305   0.00741   0.0260   0.0023   0.9584
   6.000   0.5221   0.01418   0.00865   0.0269   0.0023   0.9607
   6.250   0.5503   0.01554   0.01014   0.0264   0.0021   0.9616
   6.500   0.5888   0.01805   0.01288   0.0245   0.0020   0.9601
   6.750   0.6220   0.02100   0.01615   0.0239   0.0022   0.9599
   7.000   0.6481   0.02482   0.02034   0.0248   0.0023   0.9608
   7.250   0.6667   0.02827   0.02411   0.0268   0.0025   0.9633
   7.500   0.6774   0.03116   0.02724   0.0299   0.0026   0.9679
   7.750   0.6905   0.03446   0.03081   0.0314   0.0029   0.9693
   8.250   0.7187   0.04190   0.03875   0.0356   0.0027   0.9736
   8.500   0.7290   0.04366   0.04062   0.0380   0.0019   0.9782
   8.750   0.7327   0.04885   0.04611   0.0406   0.0022   0.9799
   9.000   0.7380   0.05221   0.04964   0.0421   0.0019   0.9823
   9.500   0.7387   0.05865   0.05637   0.0457   0.0018   0.9888
  11.000   0.6582   0.08590   0.08428   0.0426   0.0018   0.9996
  11.250   0.6351   0.09546   0.09390   0.0364   0.0020   1.0000
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