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AUGUST 160 (august160-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: AUGUST 160 (august160-il)
Reynolds number: 500,000
Max Cl/Cd: 90.31 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-august160-il-500000-n5.txt
Download as CSV file: xf-august160-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AUGUST 160                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2075   0.07147   0.06701  -0.0615   0.4425   0.0108
  -9.250  -0.2248   0.06495   0.06054  -0.0656   0.4421   0.0108
  -9.000  -0.2498   0.05772   0.05334  -0.0715   0.4418   0.0107
  -8.500  -0.3803   0.03394   0.02860  -0.0654   0.4498   0.0107
  -8.250  -0.3822   0.03069   0.02497  -0.0623   0.4460   0.0107
  -8.000  -0.3764   0.02818   0.02206  -0.0596   0.4409   0.0108
  -7.750  -0.3644   0.02643   0.01999  -0.0574   0.4355   0.0109
  -7.500  -0.3508   0.02471   0.01797  -0.0553   0.4305   0.0109
  -7.250  -0.3345   0.02324   0.01632  -0.0537   0.4250   0.0112
  -7.000  -0.3149   0.02222   0.01514  -0.0523   0.4191   0.0113
  -6.750  -0.2936   0.02156   0.01435  -0.0512   0.4137   0.0115
  -6.500  -0.2713   0.02093   0.01362  -0.0502   0.4089   0.0118
  -6.250  -0.2490   0.02014   0.01268  -0.0491   0.4041   0.0119
  -6.000  -0.2266   0.01929   0.01164  -0.0480   0.3993   0.0121
  -5.500  -0.1798   0.01778   0.00980  -0.0460   0.3909   0.0123
  -5.250  -0.1557   0.01711   0.00901  -0.0451   0.3869   0.0124
  -5.000  -0.1312   0.01655   0.00834  -0.0442   0.3827   0.0126
  -4.750  -0.1068   0.01604   0.00770  -0.0434   0.3786   0.0129
  -4.500  -0.0820   0.01560   0.00718  -0.0425   0.3752   0.0130
  -4.250  -0.0569   0.01518   0.00669  -0.0418   0.3722   0.0132
  -4.000  -0.0318   0.01482   0.00626  -0.0410   0.3687   0.0135
  -3.750  -0.0066   0.01452   0.00589  -0.0403   0.3653   0.0136
  -3.500   0.0176   0.01412   0.00546  -0.0394   0.3620   0.0139
  -3.250   0.0422   0.01383   0.00513  -0.0386   0.3587   0.0142
  -3.000   0.0676   0.01357   0.00485  -0.0379   0.3564   0.0146
  -2.750   0.0933   0.01335   0.00461  -0.0373   0.3537   0.0150
  -2.500   0.1190   0.01316   0.00439  -0.0366   0.3509   0.0153
  -2.250   0.1448   0.01299   0.00418  -0.0360   0.3480   0.0158
  -2.000   0.1707   0.01288   0.00402  -0.0354   0.3450   0.0164
  -1.750   0.1961   0.01275   0.00385  -0.0348   0.3422   0.0172
  -1.500   0.2222   0.01262   0.00371  -0.0342   0.3400   0.0180
  -1.250   0.2485   0.01252   0.00359  -0.0337   0.3380   0.0187
  -1.000   0.2749   0.01244   0.00348  -0.0332   0.3360   0.0199
  -0.750   0.3011   0.01236   0.00339  -0.0327   0.3339   0.0220
  -0.500   0.3268   0.01224   0.00332  -0.0321   0.3318   0.0346
  -0.250   0.3510   0.01200   0.00327  -0.0314   0.3298   0.0928
   0.000   0.3759   0.01187   0.00325  -0.0307   0.3278   0.1388
   0.250   0.3998   0.01169   0.00325  -0.0300   0.3259   0.2082
   0.500   0.4204   0.01126   0.00326  -0.0287   0.3242   0.3568
   0.750   0.4345   0.01051   0.00326  -0.0261   0.3231   0.5857
   1.000   0.4490   0.00974   0.00349  -0.0227   0.3220   0.8764
   1.250   0.4848   0.00990   0.00368  -0.0239   0.3202   0.9264
   1.500   0.5175   0.01004   0.00380  -0.0247   0.3186   0.9424
   1.750   0.5489   0.01019   0.00390  -0.0252   0.3169   0.9540
   2.000   0.5878   0.01037   0.00402  -0.0273   0.3152   0.9617
   2.250   0.6256   0.01055   0.00414  -0.0293   0.3134   0.9674
   2.500   0.6651   0.01073   0.00425  -0.0317   0.3118   0.9706
   2.750   0.6984   0.01091   0.00438  -0.0328   0.3102   0.9760
   3.000   0.7359   0.01111   0.00451  -0.0349   0.3084   0.9780
   3.250   0.7709   0.01125   0.00463  -0.0364   0.3073   0.9798
   3.500   0.8029   0.01136   0.00473  -0.0374   0.3064   0.9816
   3.750   0.8329   0.01147   0.00483  -0.0379   0.3051   0.9835
   4.000   0.8632   0.01159   0.00495  -0.0385   0.3037   0.9861
   4.250   0.8961   0.01172   0.00506  -0.0397   0.3024   0.9873
   4.500   0.9293   0.01186   0.00520  -0.0410   0.3011   0.9888
   4.750   0.9641   0.01201   0.00534  -0.0426   0.2999   0.9911
   5.000   0.9938   0.01217   0.00548  -0.0432   0.2987   0.9927
   5.250   1.0261   0.01233   0.00564  -0.0443   0.2974   0.9950
   5.500   1.0560   0.01249   0.00578  -0.0450   0.2960   0.9966
   5.750   1.0851   0.01267   0.00595  -0.0455   0.2945   0.9981
   6.000   1.1141   0.01288   0.00614  -0.0461   0.2932   0.9993
   6.250   1.1400   0.01309   0.00635  -0.0460   0.2919   1.0000
   6.500   1.1608   0.01321   0.00652  -0.0448   0.2908   1.0000
   6.750   1.1811   0.01337   0.00671  -0.0435   0.2899   1.0000
   7.000   1.2012   0.01352   0.00689  -0.0422   0.2887   1.0000
   7.250   1.2211   0.01365   0.00706  -0.0409   0.2867   1.0000
   7.500   1.2406   0.01382   0.00725  -0.0395   0.2853   1.0000
   7.750   1.2598   0.01400   0.00745  -0.0381   0.2840   1.0000
   8.000   1.2788   0.01417   0.00764  -0.0366   0.2823   1.0000
   8.250   1.2977   0.01437   0.00785  -0.0352   0.2811   1.0000
   8.500   1.3169   0.01459   0.00809  -0.0338   0.2802   1.0000
   8.750   1.3361   0.01483   0.00834  -0.0325   0.2792   1.0000
   9.000   1.3554   0.01509   0.00862  -0.0312   0.2781   1.0000
   9.250   1.3749   0.01537   0.00892  -0.0300   0.2771   1.0000
   9.500   1.3955   0.01557   0.00919  -0.0290   0.2761   1.0000
   9.750   1.4158   0.01580   0.00948  -0.0280   0.2749   1.0000
  10.000   1.4359   0.01602   0.00976  -0.0270   0.2733   1.0000
  10.250   1.4555   0.01626   0.01006  -0.0259   0.2715   1.0000
  10.500   1.4746   0.01652   0.01036  -0.0248   0.2700   1.0000
  10.750   1.4930   0.01680   0.01068  -0.0235   0.2682   1.0000
  11.000   1.5091   0.01710   0.01102  -0.0219   0.2668   1.0000
  11.250   1.5236   0.01742   0.01137  -0.0201   0.2651   1.0000
  11.500   1.5380   0.01779   0.01177  -0.0183   0.2635   1.0000
  11.750   1.5534   0.01817   0.01221  -0.0169   0.2615   1.0000
  12.000   1.5701   0.01854   0.01267  -0.0157   0.2597   1.0000
  12.250   1.5861   0.01895   0.01317  -0.0145   0.2576   1.0000
  12.500   1.6009   0.01944   0.01373  -0.0134   0.2548   1.0000
  12.750   1.6140   0.02005   0.01438  -0.0122   0.2518   1.0000
  13.000   1.6255   0.02081   0.01518  -0.0111   0.2493   1.0000
  13.250   1.6389   0.02156   0.01601  -0.0103   0.2470   1.0000
  13.500   1.6529   0.02236   0.01692  -0.0098   0.2442   1.0000
  13.750   1.6647   0.02335   0.01800  -0.0093   0.2407   1.0000
  14.000   1.6736   0.02464   0.01936  -0.0089   0.2371   1.0000
  14.250   1.6809   0.02618   0.02097  -0.0087   0.2330   1.0000
  14.500   1.6899   0.02766   0.02256  -0.0087   0.2294   1.0000
  14.750   1.6882   0.03025   0.02519  -0.0089   0.2218   1.0000
  15.000   1.6879   0.03279   0.02781  -0.0092   0.2160   1.0000
  15.250   1.6732   0.03689   0.03195  -0.0097   0.2089   1.0000
  15.500   1.6617   0.04070   0.03585  -0.0102   0.2034   1.0000
  15.750   1.6348   0.04618   0.04139  -0.0109   0.1971   1.0000
  16.000   1.6133   0.05112   0.04642  -0.0115   0.1916   1.0000
  16.250   1.5819   0.05736   0.05274  -0.0125   0.1849   1.0000
  16.500   1.5462   0.06435   0.05979  -0.0138   0.1761   1.0000
  16.750   1.5075   0.07194   0.06743  -0.0154   0.1684   1.0000
  17.000   1.4629   0.08049   0.07600  -0.0173   0.1602   1.0000
  17.250   1.4349   0.08709   0.08264  -0.0189   0.1541   1.0000
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