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AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: AQUILA 9.3% smoothed (aquilasm-il)
Reynolds number: 200,000
Max Cl/Cd: 74.75 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-aquilasm-il-200000.txt
Download as CSV file: xf-aquilasm-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3164   0.10198   0.09848  -0.0278   1.0000   0.0308
  -8.750  -0.3147   0.09949   0.09604  -0.0298   1.0000   0.0312
  -8.500  -0.3168   0.09745   0.09407  -0.0328   1.0000   0.0315
  -8.250  -0.2430   0.08135   0.07829  -0.0349   1.0000   0.0328
  -8.000  -0.2374   0.07799   0.07498  -0.0338   1.0000   0.0334
  -7.750  -0.2370   0.07511   0.07215  -0.0332   1.0000   0.0340
  -7.500  -0.2421   0.07276   0.06989  -0.0320   1.0000   0.0343
  -7.250  -0.2648   0.07252   0.06978  -0.0273   1.0000   0.0344
  -7.000  -0.3479   0.08155   0.07859  -0.0345   1.0000   0.0324
  -6.750  -0.3454   0.07844   0.07554  -0.0318   0.9982   0.0330
  -6.500  -0.3191   0.07404   0.07112  -0.0361   0.9923   0.0339
  -6.250  -0.2887   0.06938   0.06641  -0.0429   0.9851   0.0353
  -6.000  -0.2568   0.06452   0.06148  -0.0507   0.9763   0.0369
  -5.750  -0.2178   0.05925   0.05607  -0.0601   0.9695   0.0395
  -5.500  -0.1655   0.05563   0.05190  -0.0712   0.9592   0.0420
  -5.250  -0.1435   0.04867   0.04490  -0.0751   0.9506   0.0432
  -5.000  -0.1156   0.04501   0.04125  -0.0779   0.9431   0.0448
  -4.750  -0.0888   0.04210   0.03824  -0.0799   0.9315   0.0474
  -4.500  -0.0580   0.03950   0.03534  -0.0818   0.9194   0.0525
  -4.250  -0.0336   0.03606   0.03151  -0.0828   0.9065   0.0567
  -4.000  -0.0124   0.03376   0.02919  -0.0827   0.8943   0.0597
  -3.750   0.0119   0.03201   0.02716  -0.0823   0.8820   0.0655
  -3.500   0.0341   0.02974   0.02448  -0.0815   0.8688   0.0713
  -3.250   0.0553   0.02786   0.02255  -0.0809   0.8558   0.0753
  -3.000   0.0789   0.02638   0.02066  -0.0799   0.8432   0.0861
  -2.750   0.1018   0.02480   0.01901  -0.0793   0.8313   0.0931
  -2.500   0.1252   0.02331   0.01731  -0.0785   0.8199   0.1061
  -2.000   0.1869   0.01972   0.01242  -0.0747   0.7980   0.0552
  -1.750   0.2128   0.01777   0.01029  -0.0739   0.7869   0.0526
  -1.500   0.2396   0.01631   0.00859  -0.0730   0.7766   0.0501
  -1.250   0.2663   0.01531   0.00740  -0.0721   0.7655   0.0498
  -1.000   0.2924   0.01455   0.00653  -0.0712   0.7539   0.0515
  -0.750   0.3180   0.01389   0.00578  -0.0704   0.7430   0.0565
  -0.500   0.3431   0.01324   0.00513  -0.0696   0.7326   0.0622
  -0.250   0.3681   0.01277   0.00461  -0.0687   0.7215   0.0727
   0.000   0.3932   0.01237   0.00420  -0.0680   0.7101   0.0924
   0.250   0.4585   0.00966   0.00380  -0.0755   0.6987   1.0000
   0.500   0.4831   0.00976   0.00371  -0.0747   0.6878   1.0000
   0.750   0.5077   0.00987   0.00364  -0.0738   0.6767   1.0000
   1.000   0.5321   0.00998   0.00363  -0.0730   0.6650   1.0000
   1.250   0.5567   0.01010   0.00363  -0.0723   0.6537   1.0000
   1.500   0.5815   0.01023   0.00363  -0.0715   0.6429   1.0000
   1.750   0.6064   0.01037   0.00363  -0.0708   0.6321   1.0000
   2.000   0.6311   0.01050   0.00369  -0.0701   0.6202   1.0000
   2.250   0.6559   0.01064   0.00375  -0.0694   0.6087   1.0000
   2.500   0.6808   0.01079   0.00382  -0.0687   0.5976   1.0000
   2.750   0.7059   0.01095   0.00388  -0.0681   0.5867   1.0000
   3.000   0.7307   0.01110   0.00398  -0.0674   0.5748   1.0000
   3.250   0.7555   0.01126   0.00410  -0.0668   0.5628   1.0000
   3.500   0.7803   0.01144   0.00424  -0.0662   0.5509   1.0000
   3.750   0.8052   0.01162   0.00437  -0.0655   0.5392   1.0000
   4.000   0.8301   0.01182   0.00449  -0.0649   0.5276   1.0000
   4.250   0.8548   0.01202   0.00465  -0.0643   0.5154   1.0000
   4.500   0.8794   0.01221   0.00486  -0.0637   0.5027   1.0000
   4.750   0.9039   0.01243   0.00506  -0.0630   0.4900   1.0000
   5.000   0.9283   0.01266   0.00527  -0.0624   0.4773   1.0000
   5.250   0.9526   0.01291   0.00549  -0.0618   0.4648   1.0000
   5.500   0.9768   0.01317   0.00575  -0.0611   0.4522   1.0000
   5.750   1.0009   0.01345   0.00600  -0.0605   0.4399   1.0000
   6.000   1.0248   0.01375   0.00627  -0.0598   0.4275   1.0000
   6.250   1.0484   0.01404   0.00658  -0.0591   0.4144   1.0000
   6.500   1.0719   0.01434   0.00693  -0.0584   0.4016   1.0000
   6.750   1.0952   0.01467   0.00729  -0.0577   0.3890   1.0000
   7.000   1.1183   0.01503   0.00766  -0.0570   0.3767   1.0000
   7.250   1.1411   0.01540   0.00804  -0.0562   0.3643   1.0000
   7.500   1.1637   0.01580   0.00846  -0.0555   0.3524   1.0000
   7.750   1.1856   0.01619   0.00886  -0.0546   0.3396   1.0000
   8.000   1.2065   0.01656   0.00926  -0.0536   0.3249   1.0000
   8.250   1.2270   0.01694   0.00968  -0.0525   0.3105   1.0000
   8.500   1.2474   0.01738   0.01016  -0.0515   0.2972   1.0000
   8.750   1.2673   0.01782   0.01066  -0.0504   0.2843   1.0000
   9.000   1.2868   0.01827   0.01119  -0.0492   0.2710   1.0000
   9.250   1.3054   0.01875   0.01175  -0.0479   0.2575   1.0000
   9.500   1.3228   0.01927   0.01235  -0.0465   0.2431   1.0000
   9.750   1.3382   0.01984   0.01295  -0.0448   0.2267   1.0000
  10.000   1.3526   0.02039   0.01358  -0.0431   0.2059   1.0000
  10.250   1.3635   0.02115   0.01430  -0.0409   0.1827   1.0000
  10.500   1.3703   0.02208   0.01516  -0.0382   0.1582   1.0000
  10.750   1.3738   0.02319   0.01622  -0.0351   0.1337   1.0000
  11.000   1.3735   0.02463   0.01755  -0.0319   0.1089   1.0000
  11.250   1.3707   0.02639   0.01920  -0.0289   0.0876   1.0000
  11.500   1.3655   0.02846   0.02120  -0.0261   0.0725   1.0000
  11.750   1.3586   0.03086   0.02356  -0.0237   0.0602   1.0000
  12.000   1.3524   0.03345   0.02616  -0.0219   0.0505   1.0000
  12.250   1.3444   0.03641   0.02919  -0.0204   0.0426   1.0000
  12.500   1.3322   0.04001   0.03284  -0.0193   0.0381   1.0000
  12.750   1.3267   0.04316   0.03611  -0.0187   0.0341   1.0000
  13.000   1.3141   0.04721   0.04019  -0.0184   0.0314   1.0000
  13.250   1.3059   0.05092   0.04399  -0.0182   0.0301   1.0000
  13.500   1.3028   0.05419   0.04742  -0.0182   0.0282   1.0000
  13.750   1.2991   0.05760   0.05093  -0.0184   0.0264   1.0000
  14.000   1.2947   0.06117   0.05457  -0.0187   0.0251   1.0000
  14.250   1.2898   0.06478   0.05823  -0.0189   0.0241   1.0000
  14.500   1.2877   0.06805   0.06157  -0.0186   0.0230   1.0000
  14.750   1.2878   0.07135   0.06504  -0.0190   0.0221   1.0000
  15.000   1.2880   0.07466   0.06848  -0.0194   0.0214   1.0000
  15.250   1.2887   0.07791   0.07187  -0.0197   0.0208   1.0000
  15.500   1.2888   0.08136   0.07546  -0.0201   0.0203   1.0000
  15.750   1.2875   0.08510   0.07933  -0.0208   0.0196   1.0000
  16.000   1.2864   0.08886   0.08324  -0.0216   0.0194   1.0000
  16.250   1.2839   0.09295   0.08745  -0.0227   0.0190   1.0000
  16.500   1.2800   0.09737   0.09204  -0.0241   0.0188   1.0000
  16.750   1.2747   0.10208   0.09690  -0.0257   0.0185   1.0000
  17.000   1.2672   0.10739   0.10240  -0.0279   0.0185   1.0000
  17.250   1.2579   0.11314   0.10834  -0.0305   0.0184   1.0000
  17.500   1.2459   0.11962   0.11503  -0.0339   0.0184   1.0000
  17.750   1.2318   0.12673   0.12236  -0.0378   0.0185   1.0000
  18.000   1.2143   0.13495   0.13082  -0.0428   0.0187   1.0000
  18.250   1.1942   0.14417   0.14027  -0.0486   0.0189   1.0000
  18.500   1.1666   0.15598   0.15233  -0.0563   0.0194   1.0000
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