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AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AQUILA 9.3% smoothed (aquilasm-il)
Reynolds number: 200,000
Max Cl/Cd: 75.02 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-aquilasm-il-200000-n5.txt
Download as CSV file: xf-aquilasm-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3103   0.08945   0.08614  -0.0331   1.0000   0.0251
  -7.750  -0.3147   0.08701   0.08376  -0.0338   1.0000   0.0252
  -7.500  -0.3211   0.08463   0.08147  -0.0344   1.0000   0.0252
  -7.250  -0.3028   0.07982   0.07665  -0.0425   0.9852   0.0254
  -7.000  -0.2765   0.07441   0.07116  -0.0515   0.9701   0.0254
  -6.750  -0.2504   0.06935   0.06600  -0.0584   0.9553   0.0255
  -6.500  -0.2246   0.06458   0.06110  -0.0642   0.9405   0.0255
  -6.250  -0.2099   0.05915   0.05566  -0.0668   0.9267   0.0262
  -6.000  -0.1893   0.05549   0.05192  -0.0695   0.9113   0.0266
  -5.750  -0.1691   0.05214   0.04846  -0.0718   0.8950   0.0270
  -5.500  -0.1496   0.04891   0.04509  -0.0735   0.8790   0.0276
  -5.250  -0.1301   0.04574   0.04173  -0.0748   0.8636   0.0281
  -5.000  -0.1104   0.04270   0.03848  -0.0756   0.8490   0.0288
  -4.750  -0.0899   0.03957   0.03510  -0.0761   0.8354   0.0288
  -4.250  -0.0445   0.03261   0.02738  -0.0756   0.8109   0.0244
  -4.000  -0.0236   0.02995   0.02446  -0.0752   0.7987   0.0229
  -3.500   0.0252   0.02338   0.01677  -0.0728   0.7768   0.0193
  -3.250   0.0492   0.02146   0.01450  -0.0721   0.7660   0.0192
  -3.000   0.0742   0.01978   0.01246  -0.0713   0.7548   0.0192
  -2.750   0.0999   0.01831   0.01062  -0.0706   0.7439   0.0193
  -2.500   0.1256   0.01695   0.00899  -0.0699   0.7334   0.0197
  -2.000   0.1775   0.01532   0.00704  -0.0688   0.7119   0.0213
  -1.750   0.2038   0.01485   0.00646  -0.0684   0.7012   0.0236
  -1.500   0.2301   0.01433   0.00577  -0.0677   0.6909   0.0254
  -1.250   0.2552   0.01357   0.00495  -0.0671   0.6805   0.0270
  -1.000   0.2809   0.01314   0.00448  -0.0665   0.6697   0.0293
  -0.750   0.3069   0.01289   0.00415  -0.0660   0.6594   0.0336
  -0.500   0.3323   0.01251   0.00371  -0.0654   0.6492   0.0389
  -0.250   0.3583   0.01229   0.00342  -0.0650   0.6384   0.0470
   0.000   0.3844   0.01210   0.00316  -0.0645   0.6279   0.0579
   0.250   0.4100   0.01183   0.00297  -0.0640   0.6177   0.0994
   0.500   0.4723   0.00948   0.00293  -0.0714   0.6057   1.0000
   0.750   0.4970   0.00958   0.00288  -0.0707   0.5947   1.0000
   1.000   0.5218   0.00969   0.00285  -0.0700   0.5842   1.0000
   1.250   0.5465   0.00981   0.00283  -0.0693   0.5738   1.0000
   1.500   0.5713   0.00994   0.00283  -0.0686   0.5631   1.0000
   1.750   0.5962   0.01006   0.00286  -0.0679   0.5522   1.0000
   2.000   0.6211   0.01020   0.00290  -0.0673   0.5415   1.0000
   2.250   0.6459   0.01035   0.00295  -0.0667   0.5310   1.0000
   2.500   0.6709   0.01049   0.00302  -0.0661   0.5199   1.0000
   2.750   0.6959   0.01065   0.00312  -0.0655   0.5088   1.0000
   3.000   0.7208   0.01081   0.00322  -0.0649   0.4980   1.0000
   3.250   0.7456   0.01099   0.00332  -0.0643   0.4871   1.0000
   3.500   0.7705   0.01117   0.00345  -0.0638   0.4758   1.0000
   3.750   0.7953   0.01135   0.00361  -0.0632   0.4642   1.0000
   4.000   0.8201   0.01155   0.00377  -0.0626   0.4528   1.0000
   4.250   0.8447   0.01176   0.00394  -0.0621   0.4416   1.0000
   4.500   0.8691   0.01198   0.00412  -0.0615   0.4302   1.0000
   4.750   0.8937   0.01221   0.00434  -0.0609   0.4183   1.0000
   5.000   0.9181   0.01244   0.00456  -0.0603   0.4065   1.0000
   5.250   0.9423   0.01269   0.00480  -0.0598   0.3951   1.0000
   5.500   0.9663   0.01296   0.00505  -0.0591   0.3837   1.0000
   5.750   0.9900   0.01325   0.00534  -0.0585   0.3723   1.0000
   6.000   1.0138   0.01353   0.00563  -0.0579   0.3608   1.0000
   6.250   1.0375   0.01383   0.00594  -0.0573   0.3494   1.0000
   6.500   1.0608   0.01414   0.00627  -0.0566   0.3382   1.0000
   6.750   1.0838   0.01449   0.00664  -0.0559   0.3275   1.0000
   7.000   1.1065   0.01484   0.00701  -0.0551   0.3165   1.0000
   7.250   1.1293   0.01519   0.00740  -0.0544   0.3054   1.0000
   7.500   1.1516   0.01557   0.00783  -0.0537   0.2946   1.0000
   7.750   1.1732   0.01598   0.00826  -0.0528   0.2828   1.0000
   8.000   1.1940   0.01642   0.00871  -0.0518   0.2679   1.0000
   8.250   1.2141   0.01688   0.00918  -0.0508   0.2520   1.0000
   8.500   1.2339   0.01737   0.00971  -0.0497   0.2374   1.0000
   8.750   1.2534   0.01788   0.01025  -0.0486   0.2242   1.0000
   9.000   1.2722   0.01841   0.01082  -0.0475   0.2113   1.0000
   9.250   1.2903   0.01898   0.01143  -0.0462   0.1982   1.0000
   9.500   1.3069   0.01961   0.01208  -0.0448   0.1825   1.0000
   9.750   1.3203   0.02041   0.01284  -0.0430   0.1623   1.0000
  10.000   1.3317   0.02131   0.01368  -0.0410   0.1388   1.0000
  10.250   1.3375   0.02239   0.01464  -0.0382   0.1140   1.0000
  10.500   1.3396   0.02369   0.01580  -0.0350   0.0900   1.0000
  10.750   1.3425   0.02502   0.01706  -0.0323   0.0738   1.0000
  11.000   1.3456   0.02642   0.01844  -0.0299   0.0617   1.0000
  11.250   1.3492   0.02786   0.01991  -0.0277   0.0523   1.0000
  11.500   1.3523   0.02944   0.02155  -0.0259   0.0444   1.0000
  11.750   1.3543   0.03120   0.02336  -0.0242   0.0382   1.0000
  12.250   1.3554   0.03532   0.02761  -0.0215   0.0268   1.0000
  12.500   1.3541   0.03775   0.03011  -0.0206   0.0232   1.0000
  12.750   1.3527   0.04032   0.03279  -0.0199   0.0198   1.0000
  13.000   1.3480   0.04338   0.03591  -0.0194   0.0176   1.0000
  13.250   1.3453   0.04637   0.03907  -0.0192   0.0161   1.0000
  13.500   1.3417   0.04958   0.04242  -0.0193   0.0152   1.0000
  13.750   1.3359   0.05319   0.04614  -0.0197   0.0142   1.0000
  14.000   1.3279   0.05721   0.05028  -0.0203   0.0135   1.0000
  14.250   1.3193   0.06147   0.05470  -0.0212   0.0131   1.0000
  14.500   1.3116   0.06579   0.05917  -0.0222   0.0127   1.0000
  14.750   1.3040   0.07026   0.06379  -0.0235   0.0123   1.0000
  15.000   1.2961   0.07495   0.06863  -0.0250   0.0119   1.0000
  15.250   1.2879   0.07979   0.07362  -0.0266   0.0116   1.0000
  15.500   1.2804   0.08466   0.07863  -0.0284   0.0113   1.0000
  15.750   1.2722   0.08979   0.08388  -0.0303   0.0110   1.0000
  16.000   1.2645   0.09494   0.08916  -0.0324   0.0105   1.0000
  16.250   1.2564   0.10025   0.09459  -0.0346   0.0103   1.0000
  16.500   1.2484   0.10564   0.10010  -0.0369   0.0102   1.0000
  16.750   1.2405   0.11112   0.10570  -0.0394   0.0099   1.0000
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