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AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: AQUILA 9.3% smoothed (aquilasm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.47 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-aquilasm-il-1000000-n5.txt
Download as CSV file: xf-aquilasm-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3397   0.10476   0.10312  -0.0229   1.0000   0.0081
  -9.500  -0.3367   0.10111   0.09949  -0.0243   1.0000   0.0081
  -9.250  -0.3321   0.09802   0.09641  -0.0253   1.0000   0.0081
  -8.750  -0.3125   0.09074   0.08914  -0.0306   0.9683   0.0078
  -8.500  -0.2779   0.08274   0.08108  -0.0446   0.9477   0.0082
  -8.250  -0.2428   0.07827   0.07647  -0.0534   0.9146   0.0076
  -8.000  -0.2380   0.07504   0.07306  -0.0555   0.8696   0.0077
  -7.750  -0.2408   0.07239   0.07030  -0.0557   0.8379   0.0076
  -7.500  -0.2467   0.06958   0.06742  -0.0563   0.8136   0.0078
  -7.250  -0.2458   0.06555   0.06331  -0.0595   0.7944   0.0079
  -7.000  -0.2399   0.06193   0.05962  -0.0622   0.7793   0.0079
  -6.500  -0.2214   0.05441   0.05190  -0.0671   0.7513   0.0078
  -6.250  -0.2094   0.04942   0.04678  -0.0699   0.7394   0.0079
  -6.000  -0.1947   0.04586   0.04309  -0.0714   0.7277   0.0078
  -5.750  -0.1786   0.04202   0.03909  -0.0725   0.7170   0.0077
  -5.500  -0.1618   0.03758   0.03443  -0.0734   0.7069   0.0076
  -5.250  -0.1438   0.03304   0.02964  -0.0736   0.6968   0.0077
  -5.000  -0.1268   0.02656   0.02273  -0.0727   0.6887   0.0081
  -4.750  -0.1182   0.01567   0.01077  -0.0699   0.6822   0.0083
  -4.500  -0.0955   0.01344   0.00810  -0.0690   0.6724   0.0084
  -4.250  -0.0703   0.01252   0.00697  -0.0685   0.6628   0.0087
  -4.000  -0.0443   0.01188   0.00618  -0.0681   0.6525   0.0088
  -3.750  -0.0185   0.01110   0.00521  -0.0677   0.6430   0.0089
  -3.500   0.0075   0.01052   0.00447  -0.0672   0.6329   0.0089
  -3.250   0.0337   0.01005   0.00389  -0.0668   0.6227   0.0090
  -3.000   0.0602   0.00967   0.00341  -0.0665   0.6132   0.0091
  -2.750   0.0866   0.00936   0.00301  -0.0661   0.6034   0.0093
  -2.500   0.1133   0.00910   0.00267  -0.0658   0.5933   0.0095
  -2.250   0.1401   0.00888   0.00239  -0.0655   0.5833   0.0098
  -2.000   0.1669   0.00870   0.00213  -0.0652   0.5738   0.0103
  -1.750   0.1939   0.00855   0.00192  -0.0649   0.5636   0.0107
  -1.500   0.2210   0.00842   0.00173  -0.0647   0.5540   0.0113
  -1.250   0.2480   0.00830   0.00158  -0.0645   0.5445   0.0124
  -1.000   0.2752   0.00824   0.00147  -0.0643   0.5342   0.0138
  -0.750   0.3024   0.00817   0.00137  -0.0641   0.5248   0.0155
  -0.500   0.3296   0.00813   0.00130  -0.0639   0.5150   0.0181
  -0.250   0.3568   0.00810   0.00125  -0.0637   0.5049   0.0218
   0.000   0.3842   0.00809   0.00121  -0.0636   0.4951   0.0254
   0.250   0.4113   0.00806   0.00117  -0.0634   0.4854   0.0319
   0.500   0.4384   0.00805   0.00115  -0.0632   0.4753   0.0422
   1.000   0.4922   0.00794   0.00115  -0.0629   0.4555   0.1186
   1.250   0.5082   0.00650   0.00124  -0.0612   0.4464   0.7123
   1.500   0.5627   0.00599   0.00135  -0.0668   0.4332   0.9861
   1.750   0.6094   0.00611   0.00137  -0.0711   0.4210   1.0000
   2.000   0.6345   0.00622   0.00141  -0.0705   0.4109   1.0000
   2.250   0.6594   0.00634   0.00146  -0.0699   0.4000   1.0000
   2.500   0.6846   0.00646   0.00152  -0.0694   0.3900   1.0000
   2.750   0.7097   0.00658   0.00159  -0.0688   0.3796   1.0000
   3.000   0.7348   0.00672   0.00167  -0.0683   0.3690   1.0000
   3.500   0.7850   0.00701   0.00184  -0.0672   0.3476   1.0000
   3.750   0.8102   0.00715   0.00195  -0.0667   0.3381   1.0000
   4.000   0.8352   0.00731   0.00205  -0.0662   0.3284   1.0000
   4.250   0.8603   0.00747   0.00217  -0.0657   0.3177   1.0000
   4.500   0.8855   0.00763   0.00230  -0.0652   0.3085   1.0000
   4.750   0.9105   0.00780   0.00243  -0.0647   0.2990   1.0000
   5.000   0.9354   0.00799   0.00258  -0.0642   0.2887   1.0000
   5.250   0.9606   0.00816   0.00272  -0.0638   0.2797   1.0000
   5.500   0.9855   0.00835   0.00289  -0.0633   0.2706   1.0000
   5.750   1.0104   0.00854   0.00306  -0.0628   0.2613   1.0000
   6.000   1.0354   0.00874   0.00323  -0.0624   0.2523   1.0000
   6.250   1.0600   0.00897   0.00343  -0.0619   0.2428   1.0000
   6.500   1.0840   0.00924   0.00365  -0.0613   0.2280   1.0000
   6.750   1.1071   0.00960   0.00391  -0.0607   0.2075   1.0000
   7.000   1.1300   0.00996   0.00419  -0.0600   0.1901   1.0000
   7.250   1.1536   0.01027   0.00445  -0.0594   0.1772   1.0000
   7.500   1.1762   0.01065   0.00476  -0.0587   0.1614   1.0000
   7.750   1.1987   0.01104   0.00509  -0.0579   0.1455   1.0000
   8.000   1.2199   0.01152   0.00547  -0.0570   0.1259   1.0000
   8.250   1.2388   0.01218   0.00598  -0.0558   0.0995   1.0000
   8.500   1.2571   0.01287   0.00653  -0.0545   0.0756   1.0000
   8.750   1.2762   0.01346   0.00705  -0.0533   0.0596   1.0000
   9.000   1.2949   0.01406   0.00758  -0.0521   0.0459   1.0000
   9.250   1.3136   0.01464   0.00811  -0.0508   0.0359   1.0000
   9.500   1.3325   0.01516   0.00862  -0.0497   0.0293   1.0000
   9.750   1.3505   0.01573   0.00916  -0.0483   0.0232   1.0000
  10.000   1.3670   0.01635   0.00976  -0.0468   0.0169   1.0000
  10.250   1.3814   0.01706   0.01045  -0.0450   0.0104   1.0000
  10.500   1.3939   0.01778   0.01117  -0.0428   0.0066   1.0000
  10.750   1.4064   0.01834   0.01177  -0.0405   0.0059   1.0000
  11.000   1.4179   0.01895   0.01242  -0.0382   0.0054   1.0000
  11.250   1.4279   0.01966   0.01319  -0.0358   0.0048   1.0000
  11.500   1.4384   0.02039   0.01397  -0.0336   0.0046   1.0000
  11.750   1.4490   0.02115   0.01480  -0.0317   0.0045   1.0000
  12.000   1.4582   0.02204   0.01577  -0.0297   0.0042   1.0000
  12.250   1.4673   0.02300   0.01680  -0.0279   0.0041   1.0000
  12.500   1.4756   0.02407   0.01795  -0.0263   0.0040   1.0000
  12.750   1.4824   0.02533   0.01928  -0.0247   0.0038   1.0000
  13.000   1.4882   0.02674   0.02078  -0.0232   0.0037   1.0000
  13.250   1.4935   0.02829   0.02240  -0.0219   0.0035   1.0000
  13.500   1.4985   0.02996   0.02415  -0.0209   0.0035   1.0000
  13.750   1.5003   0.03201   0.02629  -0.0199   0.0033   1.0000
  14.000   1.5001   0.03437   0.02875  -0.0191   0.0032   1.0000
  14.250   1.4999   0.03684   0.03132  -0.0186   0.0031   1.0000
  14.500   1.4985   0.03955   0.03413  -0.0182   0.0030   1.0000
  14.750   1.4955   0.04255   0.03725  -0.0181   0.0030   1.0000
  15.000   1.4966   0.04518   0.03996  -0.0181   0.0029   1.0000
  15.250   1.4928   0.04845   0.04335  -0.0184   0.0029   1.0000
  15.500   1.4935   0.05128   0.04627  -0.0187   0.0028   1.0000
  15.750   1.4860   0.05525   0.05035  -0.0194   0.0028   1.0000
  16.000   1.4806   0.05910   0.05430  -0.0202   0.0027   1.0000
  16.250   1.4740   0.06322   0.05854  -0.0212   0.0027   1.0000
  16.500   1.4647   0.06786   0.06329  -0.0225   0.0027   1.0000
  16.750   1.4573   0.07235   0.06788  -0.0239   0.0027   1.0000
  17.000   1.4473   0.07738   0.07303  -0.0256   0.0026   1.0000
  17.250   1.4350   0.08289   0.07866  -0.0275   0.0027   1.0000
  17.500   1.4255   0.08808   0.08395  -0.0295   0.0026   1.0000
  17.750   1.4139   0.09375   0.08974  -0.0317   0.0026   1.0000
  18.000   1.4009   0.09978   0.09588  -0.0343   0.0026   1.0000
  18.250   1.3869   0.10614   0.10236  -0.0370   0.0025   1.0000
  18.500   1.3760   0.11205   0.10838  -0.0397   0.0025   1.0000
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