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AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AQUILA 9.3% smoothed (aquilasm-il)
Reynolds number: 500,000
Max Cl/Cd: 104.76 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-aquilasm-il-500000.txt
Download as CSV file: xf-aquilasm-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AQUILA 9.3% smoothed                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3083   0.08600   0.08388  -0.0300   1.0000   0.0154
  -7.750  -0.3078   0.08343   0.08135  -0.0303   1.0000   0.0159
  -7.500  -0.3106   0.08100   0.07897  -0.0302   1.0000   0.0161
  -7.250  -0.3184   0.07887   0.07692  -0.0296   0.9993   0.0163
  -7.000  -0.2933   0.07370   0.07173  -0.0385   0.9850   0.0168
  -6.750  -0.2526   0.06635   0.06429  -0.0553   0.9717   0.0183
  -6.500  -0.2156   0.06034   0.05813  -0.0658   0.9581   0.0185
  -6.250  -0.1845   0.05515   0.05279  -0.0725   0.9419   0.0186
  -6.000  -0.1715   0.04953   0.04705  -0.0754   0.9204   0.0190
  -5.750  -0.1561   0.04675   0.04414  -0.0761   0.9007   0.0193
  -5.500  -0.1402   0.04429   0.04155  -0.0764   0.8826   0.0196
  -5.250  -0.1233   0.04177   0.03887  -0.0766   0.8657   0.0201
  -5.000  -0.1049   0.03915   0.03608  -0.0768   0.8501   0.0207
  -4.750  -0.0850   0.03645   0.03316  -0.0768   0.8356   0.0218
  -4.500  -0.0566   0.03409   0.03040  -0.0761   0.8227   0.0240
  -4.250  -0.0340   0.03192   0.02787  -0.0753   0.8096   0.0243
  -4.000  -0.0200   0.02717   0.02295  -0.0753   0.7973   0.0254
  -3.750   0.0019   0.02568   0.02133  -0.0750   0.7850   0.0264
  -3.500   0.0252   0.02413   0.01958  -0.0744   0.7733   0.0277
  -3.250   0.0541   0.02403   0.01913  -0.0733   0.7619   0.0316
  -3.000   0.0746   0.02045   0.01516  -0.0725   0.7511   0.0333
  -2.750   0.0988   0.01912   0.01374  -0.0722   0.7397   0.0346
  -2.500   0.1240   0.01805   0.01249  -0.0716   0.7287   0.0364
  -2.250   0.1503   0.01713   0.01133  -0.0709   0.7183   0.0390
  -2.000   0.1786   0.01339   0.00691  -0.0688   0.7087   0.0237
  -1.750   0.2051   0.01244   0.00578  -0.0682   0.6982   0.0239
  -1.500   0.2312   0.01156   0.00473  -0.0675   0.6879   0.0246
  -1.250   0.2566   0.01081   0.00394  -0.0670   0.6774   0.0267
  -1.000   0.2829   0.01044   0.00354  -0.0665   0.6668   0.0286
  -0.750   0.3090   0.01008   0.00310  -0.0660   0.6567   0.0304
  -0.250   0.3611   0.00945   0.00236  -0.0650   0.6359   0.0393
   0.000   0.3874   0.00922   0.00208  -0.0646   0.6258   0.0479
   0.250   0.4138   0.00907   0.00190  -0.0642   0.6159   0.0654
   0.500   0.4213   0.00681   0.00194  -0.0606   0.6069   0.8268
   0.750   0.5071   0.00667   0.00186  -0.0728   0.5931   1.0000
   1.000   0.5319   0.00676   0.00184  -0.0721   0.5829   1.0000
   1.250   0.5567   0.00687   0.00184  -0.0714   0.5727   1.0000
   1.500   0.5818   0.00695   0.00185  -0.0708   0.5620   1.0000
   1.750   0.6069   0.00705   0.00188  -0.0702   0.5516   1.0000
   2.000   0.6319   0.00716   0.00191  -0.0696   0.5413   1.0000
   2.250   0.6569   0.00728   0.00195  -0.0690   0.5305   1.0000
   2.500   0.6821   0.00739   0.00201  -0.0684   0.5196   1.0000
   2.750   0.7072   0.00751   0.00208  -0.0678   0.5089   1.0000
   3.000   0.7321   0.00765   0.00215  -0.0672   0.4982   1.0000
   3.250   0.7571   0.00779   0.00223  -0.0667   0.4869   1.0000
   3.500   0.7824   0.00792   0.00234  -0.0661   0.4757   1.0000
   3.750   0.8075   0.00807   0.00244  -0.0656   0.4643   1.0000
   4.000   0.8324   0.00823   0.00256  -0.0651   0.4527   1.0000
   4.250   0.8573   0.00841   0.00268  -0.0645   0.4409   1.0000
   4.500   0.8823   0.00859   0.00283  -0.0640   0.4288   1.0000
   4.750   0.9073   0.00876   0.00298  -0.0635   0.4169   1.0000
   5.000   0.9322   0.00895   0.00314  -0.0630   0.4048   1.0000
   5.250   0.9570   0.00915   0.00331  -0.0625   0.3926   1.0000
   5.500   0.9816   0.00937   0.00351  -0.0620   0.3805   1.0000
   5.750   1.0059   0.00961   0.00372  -0.0614   0.3684   1.0000
   6.000   1.0304   0.00985   0.00393  -0.0609   0.3564   1.0000
   6.250   1.0549   0.01008   0.00415  -0.0604   0.3442   1.0000
   6.500   1.0792   0.01033   0.00441  -0.0598   0.3324   1.0000
   6.750   1.1032   0.01060   0.00466  -0.0593   0.3208   1.0000
   7.000   1.1268   0.01089   0.00493  -0.0587   0.3074   1.0000
   7.250   1.1501   0.01120   0.00522  -0.0580   0.2916   1.0000
   7.500   1.1733   0.01152   0.00551  -0.0574   0.2784   1.0000
   7.750   1.1964   0.01185   0.00583  -0.0567   0.2668   1.0000
   8.250   1.2415   0.01256   0.00653  -0.0553   0.2418   1.0000
   8.500   1.2633   0.01295   0.00690  -0.0545   0.2266   1.0000
   8.750   1.2848   0.01336   0.00729  -0.0537   0.2090   1.0000
   9.000   1.3053   0.01384   0.00772  -0.0527   0.1912   1.0000
   9.250   1.3240   0.01443   0.00824  -0.0515   0.1702   1.0000
   9.500   1.3414   0.01510   0.00880  -0.0502   0.1471   1.0000
   9.750   1.3575   0.01583   0.00945  -0.0486   0.1239   1.0000
  10.000   1.3707   0.01673   0.01021  -0.0467   0.0992   1.0000
  10.250   1.3816   0.01772   0.01108  -0.0445   0.0768   1.0000
  10.500   1.3896   0.01875   0.01202  -0.0418   0.0593   1.0000
  10.750   1.3963   0.01967   0.01291  -0.0389   0.0475   1.0000
  11.000   1.4014   0.02071   0.01392  -0.0359   0.0369   1.0000
  11.250   1.4037   0.02197   0.01515  -0.0328   0.0266   1.0000
  11.500   1.4050   0.02339   0.01656  -0.0299   0.0198   1.0000
  11.750   1.4054   0.02500   0.01822  -0.0273   0.0157   1.0000
  12.000   1.4075   0.02661   0.01989  -0.0252   0.0140   1.0000
  12.250   1.4054   0.02868   0.02207  -0.0232   0.0128   1.0000
  12.500   1.4084   0.03049   0.02399  -0.0218   0.0123   1.0000
  12.750   1.4100   0.03253   0.02616  -0.0207   0.0117   1.0000
  13.000   1.4093   0.03491   0.02865  -0.0198   0.0111   1.0000
  13.250   1.4091   0.03739   0.03123  -0.0191   0.0108   1.0000
  13.500   1.4055   0.04033   0.03429  -0.0187   0.0105   1.0000
  13.750   1.3963   0.04408   0.03814  -0.0186   0.0100   1.0000
  14.000   1.3864   0.04805   0.04224  -0.0188   0.0098   1.0000
  14.250   1.3766   0.05218   0.04649  -0.0192   0.0097   1.0000
  14.500   1.3649   0.05668   0.05112  -0.0199   0.0095   1.0000
  14.750   1.3604   0.06045   0.05501  -0.0206   0.0094   1.0000
  15.000   1.3564   0.06428   0.05896  -0.0215   0.0092   1.0000
  15.250   1.3501   0.06849   0.06329  -0.0226   0.0092   1.0000
  15.500   1.3453   0.07264   0.06755  -0.0238   0.0090   1.0000
  15.750   1.3384   0.07720   0.07222  -0.0251   0.0087   1.0000
  16.000   1.3335   0.08153   0.07666  -0.0266   0.0086   1.0000
  16.250   1.3266   0.08624   0.08148  -0.0281   0.0084   1.0000
  16.500   1.3208   0.09086   0.08621  -0.0297   0.0084   1.0000
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