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GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il)
Reynolds number: 500,000
Max Cl/Cd: 97.91 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe167-il-500000-n5.txt
Download as CSV file: xf-goe167-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4025   0.10833   0.10618  -0.0104   1.0000   0.0100
  -9.500  -0.4027   0.10316   0.10103  -0.0130   0.9912   0.0103
  -9.250  -0.3993   0.09817   0.09603  -0.0163   0.9488   0.0106
  -9.000  -0.3962   0.09569   0.09345  -0.0165   0.8904   0.0108
  -8.750  -0.3936   0.09340   0.09091  -0.0165   0.8286   0.0110
  -8.500  -0.3885   0.09060   0.08795  -0.0178   0.7916   0.0112
  -8.250  -0.3834   0.08755   0.08478  -0.0196   0.7627   0.0115
  -8.000  -0.3793   0.08432   0.08145  -0.0218   0.7367   0.0119
  -7.750  -0.3734   0.08025   0.07729  -0.0259   0.7135   0.0125
  -7.500  -0.3666   0.07306   0.07001  -0.0345   0.6960   0.0133
  -7.250  -0.3544   0.06557   0.06239  -0.0435   0.6796   0.0140
  -7.000  -0.3358   0.06279   0.05949  -0.0466   0.6596   0.0142
  -6.750  -0.3159   0.05977   0.05634  -0.0500   0.6422   0.0146
  -6.500  -0.2946   0.05632   0.05275  -0.0536   0.6271   0.0153
  -6.250  -0.2684   0.04292   0.03886  -0.0642   0.6205   0.0179
  -6.000  -0.2449   0.04093   0.03670  -0.0656   0.6069   0.0182
  -5.750  -0.2205   0.03980   0.03545  -0.0665   0.5948   0.0187
  -5.500  -0.1953   0.03819   0.03368  -0.0676   0.5848   0.0193
  -5.250  -0.1685   0.03515   0.03040  -0.0691   0.5765   0.0203
  -5.000  -0.1397   0.03020   0.02501  -0.0708   0.5704   0.0216
  -4.750  -0.1100   0.02418   0.01829  -0.0721   0.5649   0.0235
  -4.500  -0.0828   0.02228   0.01612  -0.0728   0.5587   0.0240
  -4.250  -0.0548   0.02113   0.01479  -0.0733   0.5530   0.0244
  -4.000  -0.0268   0.02041   0.01392  -0.0737   0.5472   0.0250
  -3.750   0.0015   0.01964   0.01300  -0.0741   0.5421   0.0257
  -3.500   0.0304   0.01837   0.01150  -0.0745   0.5375   0.0262
  -3.250   0.0594   0.01729   0.01020  -0.0748   0.5331   0.0266
  -3.000   0.0883   0.01638   0.00907  -0.0751   0.5293   0.0270
  -2.750   0.1173   0.01558   0.00811  -0.0754   0.5258   0.0274
  -2.500   0.1463   0.01488   0.00727  -0.0756   0.5223   0.0277
  -2.250   0.1752   0.01434   0.00661  -0.0759   0.5187   0.0281
  -2.000   0.2040   0.01390   0.00606  -0.0761   0.5151   0.0287
  -1.750   0.2329   0.01341   0.00547  -0.0763   0.5119   0.0289
  -1.500   0.2618   0.01295   0.00495  -0.0765   0.5089   0.0291
  -1.250   0.2907   0.01257   0.00452  -0.0767   0.5053   0.0294
  -1.000   0.3195   0.01227   0.00417  -0.0770   0.5013   0.0298
  -0.750   0.3482   0.01205   0.00388  -0.0772   0.4976   0.0302
  -0.500   0.3771   0.01184   0.00366  -0.0774   0.4943   0.0305
  -0.250   0.4061   0.01167   0.00348  -0.0777   0.4912   0.0308
   0.000   0.4351   0.01136   0.00314  -0.0780   0.4880   0.0314
   0.250   0.4640   0.01117   0.00292  -0.0783   0.4847   0.0321
   0.500   0.4929   0.01105   0.00277  -0.0786   0.4816   0.0331
   0.750   0.5220   0.01094   0.00268  -0.0789   0.4784   0.0345
   1.000   0.5510   0.01087   0.00261  -0.0791   0.4751   0.0354
   1.250   0.5799   0.01083   0.00257  -0.0794   0.4721   0.0362
   1.500   0.6087   0.01082   0.00253  -0.0797   0.4684   0.0374
   1.750   0.6376   0.01080   0.00251  -0.0799   0.4633   0.0393
   2.250   0.6952   0.01071   0.00255  -0.0805   0.4532   0.1060
   2.750   0.7464   0.00878   0.00271  -0.0801   0.4445   1.0000
   3.000   0.7750   0.00888   0.00277  -0.0803   0.4397   1.0000
   3.250   0.8036   0.00898   0.00284  -0.0806   0.4339   1.0000
   3.500   0.8321   0.00908   0.00291  -0.0808   0.4238   1.0000
   3.750   0.8606   0.00919   0.00299  -0.0810   0.4146   1.0000
   4.000   0.8888   0.00932   0.00308  -0.0812   0.4044   1.0000
   4.250   0.9169   0.00947   0.00320  -0.0814   0.3920   1.0000
   4.500   0.9448   0.00965   0.00332  -0.0816   0.3748   1.0000
   4.750   0.9721   0.00993   0.00349  -0.0817   0.3488   1.0000
   5.000   0.9965   0.01070   0.00390  -0.0817   0.2781   1.0000
   5.250   1.0215   0.01138   0.00437  -0.0816   0.2377   1.0000
   5.500   1.0467   0.01197   0.00481  -0.0816   0.2102   1.0000
   5.750   1.0718   0.01254   0.00524  -0.0815   0.1803   1.0000
   6.250   1.1152   0.01457   0.00666  -0.0806   0.0645   1.0000
   6.500   1.1407   0.01494   0.00704  -0.0805   0.0589   1.0000
   6.750   1.1662   0.01527   0.00742  -0.0804   0.0555   1.0000
   7.000   1.1910   0.01569   0.00784  -0.0802   0.0509   1.0000
   7.250   1.2155   0.01612   0.00828  -0.0799   0.0462   1.0000
   7.500   1.2400   0.01651   0.00867  -0.0797   0.0388   1.0000
   7.750   1.2600   0.01739   0.00940  -0.0789   0.0167   1.0000
   8.000   1.2816   0.01805   0.01010  -0.0782   0.0139   1.0000
   8.250   1.3034   0.01864   0.01076  -0.0775   0.0126   1.0000
   8.500   1.3248   0.01922   0.01141  -0.0768   0.0117   1.0000
   8.750   1.3449   0.01988   0.01216  -0.0760   0.0108   1.0000
   9.000   1.3634   0.02063   0.01298  -0.0749   0.0099   1.0000
   9.250   1.3788   0.02158   0.01402  -0.0734   0.0092   1.0000
   9.500   1.3943   0.02243   0.01495  -0.0719   0.0088   1.0000
   9.750   1.4085   0.02327   0.01588  -0.0702   0.0085   1.0000
  10.000   1.4196   0.02422   0.01691  -0.0681   0.0082   1.0000
  10.250   1.4254   0.02531   0.01811  -0.0653   0.0079   1.0000
  10.500   1.4309   0.02661   0.01949  -0.0629   0.0076   1.0000
  10.750   1.4363   0.02809   0.02106  -0.0609   0.0073   1.0000
  11.000   1.4414   0.02978   0.02284  -0.0594   0.0071   1.0000
  11.250   1.4453   0.03176   0.02491  -0.0582   0.0068   1.0000
  11.500   1.4468   0.03422   0.02745  -0.0574   0.0066   1.0000
  11.750   1.4431   0.03742   0.03077  -0.0568   0.0063   1.0000
  12.000   1.4448   0.04017   0.03362  -0.0565   0.0062   1.0000
  12.250   1.4464   0.04299   0.03655  -0.0564   0.0061   1.0000
  12.500   1.4465   0.04603   0.03970  -0.0563   0.0060   1.0000
  12.750   1.4459   0.04917   0.04297  -0.0563   0.0059   1.0000
  13.000   1.4442   0.05244   0.04634  -0.0562   0.0058   1.0000
  13.250   1.4419   0.05578   0.04978  -0.0562   0.0057   1.0000
  13.500   1.4392   0.05917   0.05328  -0.0562   0.0056   1.0000
  13.750   1.4358   0.06262   0.05683  -0.0562   0.0055   1.0000
  14.000   1.4326   0.06609   0.06040  -0.0563   0.0053   1.0000
  14.250   1.4295   0.06966   0.06407  -0.0564   0.0053   1.0000
  14.500   1.4266   0.07324   0.06775  -0.0567   0.0052   1.0000
  14.750   1.4238   0.07687   0.07147  -0.0571   0.0051   1.0000
  15.000   1.4210   0.08056   0.07526  -0.0575   0.0050   1.0000
  15.250   1.4182   0.08434   0.07913  -0.0580   0.0049   1.0000
  15.500   1.4153   0.08816   0.08304  -0.0586   0.0048   1.0000
  15.750   1.4123   0.09202   0.08700  -0.0593   0.0048   1.0000
  16.000   1.4089   0.09603   0.09112  -0.0601   0.0047   1.0000
  16.250   1.4055   0.10010   0.09528  -0.0611   0.0046   1.0000
  16.500   1.4019   0.10422   0.09950  -0.0621   0.0046   1.0000
  16.750   1.3975   0.10852   0.10389  -0.0632   0.0045   1.0000
  17.000   1.3926   0.11291   0.10837  -0.0644   0.0044   1.0000
  17.250   1.3867   0.11748   0.11304  -0.0657   0.0044   1.0000
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