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GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il)
Reynolds number: 1,000,000
Max Cl/Cd: 108.62 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe167-il-1000000-n5.txt
Download as CSV file: xf-goe167-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4203   0.08494   0.08223  -0.0196   0.6319   0.0088
  -8.250  -0.4175   0.08089   0.07814  -0.0233   0.6183   0.0092
  -8.000  -0.4208   0.06921   0.06643  -0.0372   0.6131   0.0106
  -7.750  -0.4035   0.06586   0.06299  -0.0415   0.5998   0.0108
  -7.500  -0.3846   0.06269   0.05973  -0.0453   0.5877   0.0110
  -7.250  -0.3647   0.05923   0.05618  -0.0493   0.5771   0.0114
  -6.750  -0.3243   0.04167   0.03811  -0.0639   0.5650   0.0141
  -6.250  -0.2786   0.02333   0.01861  -0.0704   0.5548   0.0181
  -6.000  -0.2511   0.02297   0.01816  -0.0707   0.5477   0.0183
  -5.750  -0.2236   0.02236   0.01742  -0.0711   0.5418   0.0185
  -5.500  -0.1960   0.02157   0.01651  -0.0715   0.5366   0.0188
  -5.250  -0.1682   0.02089   0.01570  -0.0719   0.5311   0.0191
  -5.000  -0.1403   0.02001   0.01467  -0.0723   0.5264   0.0196
  -4.750  -0.1120   0.01824   0.01264  -0.0728   0.5222   0.0202
  -4.500  -0.0835   0.01673   0.01087  -0.0732   0.5181   0.0210
  -4.250  -0.0549   0.01587   0.00983  -0.0735   0.5143   0.0217
  -4.000  -0.0261   0.01511   0.00890  -0.0738   0.5111   0.0222
  -3.750   0.0027   0.01448   0.00815  -0.0741   0.5080   0.0224
  -3.500   0.0316   0.01392   0.00746  -0.0744   0.5047   0.0226
  -3.250   0.0605   0.01347   0.00691  -0.0747   0.5013   0.0228
  -3.000   0.0894   0.01303   0.00637  -0.0750   0.4979   0.0229
  -2.750   0.1184   0.01263   0.00590  -0.0752   0.4953   0.0230
  -2.500   0.1474   0.01223   0.00543  -0.0755   0.4923   0.0231
  -2.250   0.1763   0.01173   0.00486  -0.0758   0.4887   0.0232
  -2.000   0.2051   0.01091   0.00394  -0.0761   0.4850   0.0239
  -1.750   0.2340   0.01056   0.00354  -0.0764   0.4816   0.0242
  -1.500   0.2631   0.01026   0.00322  -0.0767   0.4788   0.0246
  -1.250   0.2922   0.01005   0.00300  -0.0770   0.4757   0.0250
  -1.000   0.3213   0.00990   0.00282  -0.0773   0.4723   0.0255
  -0.750   0.3503   0.00977   0.00267  -0.0775   0.4687   0.0260
  -0.500   0.3795   0.00966   0.00254  -0.0778   0.4659   0.0265
  -0.250   0.4086   0.00954   0.00242  -0.0781   0.4637   0.0270
   0.000   0.4378   0.00944   0.00231  -0.0784   0.4612   0.0275
   0.250   0.4669   0.00936   0.00221  -0.0787   0.4580   0.0279
   0.500   0.4960   0.00930   0.00213  -0.0790   0.4548   0.0283
   0.750   0.5251   0.00925   0.00206  -0.0793   0.4504   0.0286
   1.000   0.5542   0.00920   0.00200  -0.0796   0.4443   0.0290
   1.250   0.5832   0.00919   0.00197  -0.0799   0.4397   0.0296
   1.500   0.6122   0.00918   0.00195  -0.0802   0.4357   0.0301
   1.750   0.6412   0.00916   0.00193  -0.0805   0.4306   0.0305
   2.000   0.6701   0.00917   0.00194  -0.0808   0.4247   0.0309
   2.250   0.6990   0.00918   0.00192  -0.0810   0.4200   0.0338
   2.500   0.7279   0.00919   0.00195  -0.0813   0.4127   0.0397
   2.750   0.7567   0.00915   0.00202  -0.0817   0.4040   0.1102
   3.250   0.8082   0.00749   0.00227  -0.0816   0.3760   1.0000
   3.500   0.8364   0.00770   0.00238  -0.0818   0.3544   1.0000
   3.750   0.8622   0.00843   0.00272  -0.0819   0.2799   1.0000
   4.000   0.8885   0.00903   0.00307  -0.0821   0.2328   1.0000
   4.250   0.9161   0.00933   0.00329  -0.0822   0.2164   1.0000
   4.500   0.9437   0.00960   0.00349  -0.0824   0.2044   1.0000
   4.750   0.9712   0.00986   0.00369  -0.0826   0.1915   1.0000
   5.000   0.9950   0.01082   0.00423  -0.0825   0.1132   1.0000
   5.250   1.0194   0.01161   0.00480  -0.0823   0.0624   1.0000
   5.500   1.0465   0.01186   0.00503  -0.0824   0.0571   1.0000
   5.750   1.0735   0.01211   0.00528  -0.0825   0.0542   1.0000
   6.000   1.1001   0.01240   0.00555  -0.0825   0.0502   1.0000
   6.250   1.1267   0.01268   0.00583  -0.0826   0.0464   1.0000
   6.500   1.1535   0.01291   0.00607  -0.0826   0.0450   1.0000
   6.750   1.1795   0.01323   0.00636  -0.0826   0.0391   1.0000
   7.000   1.2030   0.01388   0.00686  -0.0822   0.0165   1.0000
   7.250   1.2281   0.01429   0.00727  -0.0820   0.0128   1.0000
   7.500   1.2533   0.01464   0.00765  -0.0819   0.0117   1.0000
   7.750   1.2779   0.01505   0.00809  -0.0816   0.0105   1.0000
   8.000   1.3017   0.01553   0.00861  -0.0813   0.0091   1.0000
   8.250   1.3259   0.01593   0.00903  -0.0810   0.0086   1.0000
   8.500   1.3495   0.01636   0.00950  -0.0806   0.0081   1.0000
   8.750   1.3725   0.01682   0.01001  -0.0801   0.0075   1.0000
   9.000   1.3946   0.01735   0.01056  -0.0795   0.0070   1.0000
   9.250   1.4153   0.01798   0.01123  -0.0787   0.0065   1.0000
   9.500   1.4357   0.01858   0.01187  -0.0779   0.0062   1.0000
   9.750   1.4562   0.01913   0.01246  -0.0771   0.0059   1.0000
  10.000   1.4755   0.01972   0.01311  -0.0761   0.0056   1.0000
  10.250   1.4934   0.02038   0.01382  -0.0750   0.0053   1.0000
  10.500   1.5097   0.02107   0.01456  -0.0736   0.0051   1.0000
  10.750   1.5240   0.02182   0.01536  -0.0719   0.0049   1.0000
  11.000   1.5344   0.02267   0.01626  -0.0696   0.0047   1.0000
  11.250   1.5396   0.02375   0.01740  -0.0667   0.0045   1.0000
  11.500   1.5421   0.02520   0.01895  -0.0639   0.0043   1.0000
  11.750   1.5481   0.02661   0.02045  -0.0620   0.0043   1.0000
  12.000   1.5546   0.02816   0.02209  -0.0606   0.0042   1.0000
  12.250   1.5601   0.02996   0.02397  -0.0594   0.0041   1.0000
  12.500   1.5649   0.03201   0.02611  -0.0586   0.0040   1.0000
  12.750   1.5689   0.03428   0.02848  -0.0581   0.0040   1.0000
  13.000   1.5718   0.03680   0.03109  -0.0577   0.0039   1.0000
  13.250   1.5741   0.03948   0.03387  -0.0575   0.0038   1.0000
  13.500   1.5754   0.04231   0.03679  -0.0574   0.0037   1.0000
  13.750   1.5761   0.04524   0.03981  -0.0574   0.0036   1.0000
  14.000   1.5760   0.04832   0.04299  -0.0574   0.0035   1.0000
  14.250   1.5752   0.05145   0.04621  -0.0574   0.0035   1.0000
  14.500   1.5738   0.05466   0.04950  -0.0575   0.0034   1.0000
  14.750   1.5713   0.05802   0.05294  -0.0576   0.0033   1.0000
  15.000   1.5682   0.06146   0.05646  -0.0578   0.0033   1.0000
  15.250   1.5641   0.06508   0.06017  -0.0580   0.0032   1.0000
  15.500   1.5601   0.06877   0.06395  -0.0584   0.0031   1.0000
  15.750   1.5557   0.07261   0.06786  -0.0588   0.0031   1.0000
  16.000   1.5496   0.07669   0.07204  -0.0594   0.0031   1.0000
  16.250   1.5429   0.08097   0.07640  -0.0600   0.0030   1.0000
  16.500   1.5356   0.08541   0.08094  -0.0608   0.0030   1.0000
  16.750   1.5270   0.09010   0.08573  -0.0618   0.0029   1.0000
  17.000   1.5175   0.09496   0.09069  -0.0628   0.0029   1.0000
  17.250   1.5064   0.10018   0.09602  -0.0641   0.0028   1.0000
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