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S7012 8.75% (s7012-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S7012 8.75% (s7012-il)
Reynolds number: 100,000
Max Cl/Cd: 52.75 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s7012-il-100000-n5.txt
Download as CSV file: xf-s7012-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7012 8.75%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4756   0.09911   0.09408  -0.0162   1.0000   0.0269
  -9.000  -0.4738   0.09507   0.09009  -0.0179   1.0000   0.0268
  -8.750  -0.4724   0.09107   0.08614  -0.0195   1.0000   0.0264
  -8.500  -0.4718   0.08701   0.08213  -0.0215   1.0000   0.0261
  -8.250  -0.4722   0.08291   0.07810  -0.0234   1.0000   0.0255
  -8.000  -0.4752   0.07845   0.07372  -0.0261   1.0000   0.0256
  -7.750  -0.4794   0.07400   0.06934  -0.0289   1.0000   0.0248
  -7.500  -0.4812   0.06820   0.06356  -0.0346   1.0000   0.0245
  -7.250  -0.4814   0.06254   0.05784  -0.0386   1.0000   0.0239
  -7.000  -0.4800   0.05705   0.05223  -0.0416   1.0000   0.0237
  -6.750  -0.4761   0.05175   0.04673  -0.0436   1.0000   0.0233
  -6.500  -0.4692   0.04662   0.04131  -0.0449   1.0000   0.0227
  -6.250  -0.4593   0.04147   0.03573  -0.0455   1.0000   0.0219
  -6.000  -0.4456   0.03664   0.03028  -0.0456   1.0000   0.0211
  -5.750  -0.4281   0.03294   0.02604  -0.0452   1.0000   0.0207
  -5.500  -0.4086   0.03000   0.02263  -0.0446   1.0000   0.0206
  -5.250  -0.3877   0.02751   0.01973  -0.0438   1.0000   0.0206
  -5.000  -0.3661   0.02538   0.01727  -0.0430   1.0000   0.0208
  -4.750  -0.3440   0.02355   0.01517  -0.0422   1.0000   0.0211
  -4.500  -0.3217   0.02199   0.01340  -0.0413   1.0000   0.0215
  -4.250  -0.2995   0.02064   0.01190  -0.0403   1.0000   0.0223
  -4.000  -0.2773   0.01947   0.01059  -0.0394   1.0000   0.0232
  -3.750  -0.2552   0.01854   0.00956  -0.0385   1.0000   0.0251
  -3.500  -0.2310   0.01780   0.00870  -0.0380   0.9991   0.0283
  -3.250  -0.1924   0.01668   0.00750  -0.0405   0.9907   0.0342
  -3.000  -0.1537   0.01567   0.00639  -0.0428   0.9820   0.0492
  -2.750  -0.1183   0.01394   0.00575  -0.0455   0.9731   0.2339
  -2.500  -0.0859   0.01266   0.00555  -0.0471   0.9629   0.4816
  -2.250  -0.0542   0.01221   0.00558  -0.0472   0.9521   0.6395
  -2.000  -0.0214   0.01207   0.00546  -0.0475   0.9403   0.7194
  -1.750   0.0101   0.01196   0.00532  -0.0474   0.9273   0.7707
  -1.500   0.0402   0.01184   0.00516  -0.0470   0.9128   0.8105
  -1.250   0.0695   0.01173   0.00496  -0.0465   0.8972   0.8459
  -1.000   0.0993   0.01161   0.00477  -0.0461   0.8809   0.8786
  -0.750   0.1325   0.01148   0.00456  -0.0464   0.8643   0.9107
  -0.500   0.1720   0.01137   0.00433  -0.0482   0.8474   0.9422
  -0.250   0.2167   0.01126   0.00406  -0.0513   0.8296   0.9724
   0.000   0.2558   0.01121   0.00386  -0.0536   0.8088   1.0000
   0.250   0.2830   0.01126   0.00375  -0.0534   0.7882   1.0000
   0.500   0.3099   0.01134   0.00368  -0.0532   0.7675   1.0000
   0.750   0.3370   0.01144   0.00364  -0.0530   0.7475   1.0000
   1.000   0.3641   0.01157   0.00363  -0.0528   0.7283   1.0000
   1.250   0.3909   0.01171   0.00367  -0.0526   0.7087   1.0000
   1.500   0.4177   0.01186   0.00371  -0.0523   0.6900   1.0000
   1.750   0.4445   0.01203   0.00377  -0.0520   0.6720   1.0000
   2.000   0.4711   0.01221   0.00388  -0.0517   0.6535   1.0000
   2.250   0.4977   0.01240   0.00402  -0.0514   0.6356   1.0000
   2.500   0.5243   0.01260   0.00416  -0.0510   0.6183   1.0000
   2.750   0.5508   0.01282   0.00431  -0.0507   0.6015   1.0000
   3.000   0.5773   0.01304   0.00450  -0.0504   0.5842   1.0000
   3.250   0.6037   0.01327   0.00474  -0.0501   0.5666   1.0000
   3.500   0.6300   0.01351   0.00497  -0.0497   0.5490   1.0000
   3.750   0.6561   0.01376   0.00520  -0.0493   0.5316   1.0000
   4.000   0.6822   0.01402   0.00547  -0.0489   0.5137   1.0000
   4.250   0.7082   0.01429   0.00580  -0.0486   0.4950   1.0000
   4.500   0.7339   0.01458   0.00611  -0.0481   0.4756   1.0000
   4.750   0.7594   0.01487   0.00644  -0.0477   0.4550   1.0000
   5.000   0.7847   0.01519   0.00678  -0.0472   0.4332   1.0000
   5.250   0.8099   0.01552   0.00720  -0.0467   0.4100   1.0000
   5.500   0.8346   0.01588   0.00760  -0.0461   0.3848   1.0000
   5.750   0.8588   0.01628   0.00803  -0.0455   0.3557   1.0000
   6.000   0.8825   0.01675   0.00850  -0.0449   0.3239   1.0000
   6.250   0.9055   0.01731   0.00903  -0.0442   0.2904   1.0000
   6.500   0.9281   0.01796   0.00969  -0.0435   0.2531   1.0000
   6.750   0.9494   0.01877   0.01041  -0.0427   0.2121   1.0000
   7.000   0.9693   0.01979   0.01125  -0.0419   0.1664   1.0000
   7.250   0.9875   0.02109   0.01225  -0.0411   0.1121   1.0000
   7.500   1.0037   0.02271   0.01348  -0.0401   0.0623   1.0000
   7.750   1.0197   0.02439   0.01504  -0.0388   0.0379   1.0000
   8.000   1.0354   0.02605   0.01678  -0.0375   0.0273   1.0000
   8.250   1.0511   0.02760   0.01850  -0.0361   0.0231   1.0000
   8.500   1.0632   0.02950   0.02052  -0.0344   0.0210   1.0000
   8.750   1.0770   0.03117   0.02243  -0.0328   0.0197   1.0000
   9.000   1.0897   0.03299   0.02445  -0.0312   0.0187   1.0000
   9.250   1.1021   0.03493   0.02658  -0.0296   0.0179   1.0000
   9.500   1.1141   0.03701   0.02885  -0.0280   0.0171   1.0000
   9.750   1.1256   0.03923   0.03128  -0.0266   0.0166   1.0000
  10.000   1.1354   0.04151   0.03375  -0.0251   0.0160   1.0000
  10.250   1.1411   0.04382   0.03628  -0.0234   0.0153   1.0000
  10.500   1.1435   0.04653   0.03915  -0.0217   0.0148   1.0000
  10.750   1.1423   0.04968   0.04253  -0.0201   0.0143   1.0000
  11.000   1.1391   0.05252   0.04570  -0.0187   0.0140   1.0000
  11.250   1.1332   0.05584   0.04932  -0.0180   0.0137   1.0000
  11.500   1.1244   0.05966   0.05343  -0.0180   0.0135   1.0000
  11.750   1.1139   0.06398   0.05802  -0.0188   0.0135   1.0000
  12.000   1.1012   0.06890   0.06320  -0.0205   0.0135   1.0000
  12.250   1.0867   0.07451   0.06904  -0.0232   0.0134   1.0000
  12.500   1.0711   0.08076   0.07550  -0.0267   0.0135   1.0000
  12.750   1.0543   0.08772   0.08266  -0.0311   0.0136   1.0000
  13.000   1.0366   0.09541   0.09053  -0.0361   0.0137   1.0000
  13.250   1.0182   0.10385   0.09911  -0.0416   0.0139   1.0000
  13.500   1.0009   0.11266   0.10803  -0.0473   0.0141   1.0000
  13.750   0.9839   0.12201   0.11746  -0.0532   0.0143   1.0000
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