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AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: AQUILA 9.3% smoothed (aquilasm-il)
Reynolds number: 100,000
Max Cl/Cd: 51.58 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-aquilasm-il-100000.txt
Download as CSV file: xf-aquilasm-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3067   0.09390   0.08925  -0.0297   1.0000   0.0641
  -7.750  -0.3088   0.09161   0.08705  -0.0308   1.0000   0.0658
  -7.500  -0.3169   0.08988   0.08544  -0.0316   1.0000   0.0669
  -7.250  -0.3271   0.08834   0.08403  -0.0340   1.0000   0.0678
  -7.000  -0.3360   0.08692   0.08269  -0.0364   1.0000   0.0683
  -6.750  -0.3487   0.08596   0.08175  -0.0368   1.0000   0.0686
  -6.500  -0.3600   0.08497   0.08075  -0.0357   1.0000   0.0687
  -6.250  -0.3675   0.08150   0.07738  -0.0333   1.0000   0.0693
  -6.000  -0.3709   0.07780   0.07385  -0.0282   1.0000   0.0704
  -5.750  -0.3763   0.07570   0.07182  -0.0248   1.0000   0.0715
  -5.500  -0.3611   0.07245   0.06859  -0.0265   0.9961   0.0743
  -5.250  -0.3018   0.06884   0.06430  -0.0452   0.9838   0.0837
  -5.000  -0.2866   0.06246   0.05828  -0.0439   0.9776   0.0870
  -4.750  -0.2413   0.05877   0.05411  -0.0539   0.9675   0.0992
  -4.500  -0.2155   0.05425   0.04978  -0.0552   0.9601   0.1042
  -4.250  -0.1790   0.05044   0.04571  -0.0609   0.9504   0.1165
  -4.000  -0.1401   0.04683   0.04192  -0.0657   0.9431   0.1317
  -3.750  -0.1096   0.04385   0.03883  -0.0683   0.9330   0.1485
  -3.500  -0.0679   0.04071   0.03553  -0.0730   0.9274   0.1777
  -3.250  -0.0406   0.03836   0.03316  -0.0742   0.9167   0.2106
  -2.750   0.0127   0.03418   0.02911  -0.0746   0.8996   0.3399
  -2.500   0.0311   0.03223   0.02733  -0.0720   0.8888   0.4003
  -2.250   0.1006   0.02875   0.02279  -0.0814   0.8826   0.3069
  -2.000   0.1669   0.02517   0.01703  -0.0818   0.8726   0.0875
  -1.750   0.2014   0.02387   0.01533  -0.0816   0.8631   0.0813
  -1.500   0.2358   0.02269   0.01384  -0.0817   0.8540   0.0829
  -1.250   0.2635   0.02146   0.01248  -0.0809   0.8423   0.0847
  -1.000   0.2915   0.02027   0.01130  -0.0802   0.8313   0.0878
  -0.750   0.3210   0.01947   0.01043  -0.0795   0.8218   0.0975
  -0.500   0.3451   0.01862   0.00967  -0.0782   0.8103   0.1084
  -0.250   0.4142   0.01486   0.00842  -0.0851   0.8011   1.0000
   0.000   0.4388   0.01496   0.00807  -0.0837   0.7895   1.0000
   0.250   0.4641   0.01501   0.00783  -0.0825   0.7788   1.0000
   0.500   0.4869   0.01517   0.00780  -0.0812   0.7658   1.0000
   0.750   0.5099   0.01535   0.00780  -0.0800   0.7531   1.0000
   1.000   0.5334   0.01552   0.00781  -0.0788   0.7408   1.0000
   1.250   0.5576   0.01567   0.00782  -0.0777   0.7290   1.0000
   1.500   0.5826   0.01578   0.00778  -0.0767   0.7178   1.0000
   1.750   0.6073   0.01592   0.00779  -0.0757   0.7061   1.0000
   2.000   0.6310   0.01613   0.00790  -0.0747   0.6933   1.0000
   2.250   0.6550   0.01633   0.00802  -0.0737   0.6808   1.0000
   2.500   0.6794   0.01653   0.00814  -0.0728   0.6685   1.0000
   2.750   0.7043   0.01671   0.00824  -0.0720   0.6568   1.0000
   3.000   0.7300   0.01685   0.00827  -0.0711   0.6453   1.0000
   3.250   0.7546   0.01705   0.00841  -0.0703   0.6328   1.0000
   3.500   0.7786   0.01729   0.00864  -0.0694   0.6197   1.0000
   3.750   0.8029   0.01754   0.00886  -0.0686   0.6068   1.0000
   4.000   0.8273   0.01779   0.00907  -0.0677   0.5940   1.0000
   4.250   0.8519   0.01803   0.00928  -0.0669   0.5813   1.0000
   4.500   0.8768   0.01828   0.00952  -0.0662   0.5688   1.0000
   4.750   0.9020   0.01851   0.00970  -0.0655   0.5564   1.0000
   5.000   0.9273   0.01875   0.00989  -0.0648   0.5440   1.0000
   5.250   0.9510   0.01907   0.01023  -0.0639   0.5305   1.0000
   5.500   0.9748   0.01941   0.01062  -0.0631   0.5171   1.0000
   5.750   0.9985   0.01976   0.01100  -0.0623   0.5037   1.0000
   6.000   1.0222   0.02012   0.01139  -0.0615   0.4905   1.0000
   6.250   1.0459   0.02051   0.01180  -0.0607   0.4775   1.0000
   6.500   1.0696   0.02091   0.01226  -0.0600   0.4646   1.0000
   6.750   1.0935   0.02132   0.01270  -0.0592   0.4521   1.0000
   7.000   1.1175   0.02172   0.01311  -0.0585   0.4395   1.0000
   7.250   1.1420   0.02214   0.01351  -0.0578   0.4272   1.0000
   7.500   1.1642   0.02262   0.01411  -0.0569   0.4140   1.0000
   7.750   1.1860   0.02314   0.01474  -0.0559   0.4009   1.0000
   8.000   1.2076   0.02366   0.01536  -0.0550   0.3877   1.0000
   8.250   1.2290   0.02418   0.01596  -0.0539   0.3743   1.0000
   8.500   1.2500   0.02464   0.01652  -0.0528   0.3602   1.0000
   8.750   1.2701   0.02503   0.01697  -0.0516   0.3451   1.0000
   9.000   1.2895   0.02542   0.01741  -0.0502   0.3297   1.0000
   9.250   1.3081   0.02586   0.01790  -0.0488   0.3143   1.0000
   9.500   1.3257   0.02633   0.01845  -0.0473   0.2988   1.0000
   9.750   1.3413   0.02689   0.01910  -0.0456   0.2830   1.0000
  10.000   1.3531   0.02749   0.01988  -0.0434   0.2660   1.0000
  10.250   1.3632   0.02813   0.02065  -0.0410   0.2481   1.0000
  10.500   1.3702   0.02879   0.02136  -0.0382   0.2291   1.0000
  10.750   1.3716   0.02970   0.02237  -0.0348   0.2085   1.0000
  11.000   1.3668   0.03077   0.02346  -0.0308   0.1881   1.0000
  11.250   1.3580   0.03225   0.02494  -0.0268   0.1672   1.0000
  11.500   1.3478   0.03422   0.02682  -0.0235   0.1476   1.0000
  11.750   1.3372   0.03666   0.02920  -0.0209   0.1291   1.0000
  12.000   1.3275   0.03943   0.03193  -0.0191   0.1134   1.0000
  12.250   1.3178   0.04251   0.03498  -0.0177   0.1003   1.0000
  12.500   1.3085   0.04583   0.03827  -0.0167   0.0893   1.0000
  12.750   1.3000   0.04927   0.04166  -0.0159   0.0801   1.0000
  13.000   1.2919   0.05282   0.04514  -0.0153   0.0715   1.0000
  13.250   1.2878   0.05624   0.04870  -0.0148   0.0643   1.0000
  13.500   1.2883   0.05932   0.05171  -0.0137   0.0579   1.0000
  13.750   1.2874   0.06261   0.05514  -0.0134   0.0531   1.0000
  14.000   1.2943   0.06538   0.05783  -0.0123   0.0483   1.0000
  14.250   1.2921   0.06897   0.06169  -0.0123   0.0460   1.0000
  14.500   1.2918   0.07256   0.06552  -0.0123   0.0440   1.0000
  14.750   1.2924   0.07613   0.06925  -0.0123   0.0422   1.0000
  15.000   1.2957   0.07967   0.07290  -0.0122   0.0408   1.0000
  15.250   1.2993   0.08398   0.07734  -0.0119   0.0397   1.0000
  15.500   1.2898   0.08950   0.08310  -0.0129   0.0393   1.0000
  15.750   1.2725   0.09540   0.08924  -0.0152   0.0392   1.0000
  16.000   1.2570   0.10139   0.09546  -0.0177   0.0393   1.0000
  16.250   1.2379   0.10813   0.10244  -0.0210   0.0393   1.0000
  16.500   1.2184   0.11499   0.10956  -0.0253   0.0396   1.0000
  16.750   1.1930   0.12350   0.11832  -0.0311   0.0400   1.0000
  17.000   1.1027   0.14954   0.14484  -0.0506   0.0452   1.0000
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