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S7012 8.75% (s7012-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S7012 8.75% (s7012-il)
Reynolds number: 200,000
Max Cl/Cd: 67.47 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s7012-il-200000-n5.txt
Download as CSV file: xf-s7012-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4720   0.08826   0.08474  -0.0190   1.0000   0.0172
  -8.500  -0.4738   0.08365   0.08018  -0.0212   1.0000   0.0159
  -8.250  -0.4843   0.07561   0.07221  -0.0262   1.0000   0.0132
  -8.000  -0.4900   0.07111   0.06777  -0.0289   1.0000   0.0130
  -7.750  -0.4941   0.06550   0.06220  -0.0347   1.0000   0.0128
  -7.500  -0.4956   0.05943   0.05606  -0.0395   1.0000   0.0125
  -7.250  -0.4954   0.05369   0.05019  -0.0426   1.0000   0.0123
  -7.000  -0.4932   0.04800   0.04430  -0.0445   1.0000   0.0119
  -6.750  -0.4881   0.04243   0.03844  -0.0455   1.0000   0.0116
  -6.500  -0.4792   0.03732   0.03296  -0.0457   1.0000   0.0113
  -6.250  -0.4668   0.03262   0.02780  -0.0455   1.0000   0.0111
  -6.000  -0.4509   0.02875   0.02343  -0.0449   1.0000   0.0110
  -5.750  -0.4324   0.02569   0.01991  -0.0441   1.0000   0.0111
  -5.500  -0.4121   0.02350   0.01732  -0.0433   1.0000   0.0116
  -5.250  -0.3907   0.02190   0.01538  -0.0424   1.0000   0.0126
  -5.000  -0.3600   0.02020   0.01331  -0.0432   0.9970   0.0132
  -4.750  -0.3248   0.01841   0.01123  -0.0448   0.9918   0.0133
  -4.500  -0.2896   0.01696   0.00958  -0.0464   0.9858   0.0134
  -4.250  -0.2557   0.01575   0.00822  -0.0477   0.9789   0.0136
  -4.000  -0.2207   0.01452   0.00691  -0.0494   0.9723   0.0141
  -3.750  -0.1870   0.01364   0.00595  -0.0508   0.9638   0.0150
  -3.500  -0.1509   0.01299   0.00520  -0.0526   0.9562   0.0163
  -3.250  -0.1169   0.01246   0.00453  -0.0538   0.9456   0.0188
  -3.000  -0.0829   0.01184   0.00392  -0.0551   0.9344   0.0313
  -2.750  -0.0496   0.01093   0.00344  -0.0566   0.9219   0.1268
  -2.500  -0.0177   0.01001   0.00316  -0.0580   0.9077   0.2844
  -2.250   0.0123   0.00915   0.00296  -0.0589   0.8914   0.4670
  -2.000   0.0409   0.00872   0.00291  -0.0588   0.8736   0.5896
  -1.750   0.0687   0.00857   0.00286  -0.0583   0.8540   0.6619
  -1.500   0.0959   0.00851   0.00277  -0.0577   0.8332   0.7040
  -1.250   0.1223   0.00848   0.00267  -0.0569   0.8121   0.7350
  -1.000   0.1482   0.00848   0.00260  -0.0560   0.7907   0.7617
  -0.750   0.1736   0.00849   0.00254  -0.0550   0.7698   0.7853
  -0.500   0.1986   0.00851   0.00248  -0.0540   0.7492   0.8072
   0.000   0.2478   0.00856   0.00239  -0.0519   0.7101   0.8491
   0.250   0.2720   0.00859   0.00236  -0.0507   0.6913   0.8713
   0.500   0.2967   0.00863   0.00232  -0.0497   0.6732   0.8946
   0.750   0.3232   0.00865   0.00228  -0.0491   0.6551   0.9205
   1.000   0.3548   0.00869   0.00224  -0.0496   0.6366   0.9508
   1.250   0.3914   0.00875   0.00221  -0.0515   0.6179   0.9942
   1.500   0.4189   0.00889   0.00224  -0.0515   0.6011   1.0000
   1.750   0.4460   0.00904   0.00230  -0.0514   0.5845   1.0000
   2.000   0.4731   0.00920   0.00237  -0.0513   0.5685   1.0000
   2.250   0.5002   0.00936   0.00248  -0.0512   0.5525   1.0000
   2.500   0.5272   0.00953   0.00258  -0.0511   0.5364   1.0000
   2.750   0.5542   0.00971   0.00270  -0.0509   0.5203   1.0000
   3.000   0.5811   0.00990   0.00283  -0.0508   0.5046   1.0000
   3.250   0.6080   0.01009   0.00301  -0.0506   0.4890   1.0000
   3.500   0.6348   0.01029   0.00318  -0.0505   0.4730   1.0000
   3.750   0.6617   0.01049   0.00336  -0.0503   0.4557   1.0000
   4.000   0.6883   0.01071   0.00356  -0.0501   0.4372   1.0000
   4.250   0.7147   0.01095   0.00380  -0.0499   0.4181   1.0000
   4.500   0.7412   0.01119   0.00404  -0.0497   0.3984   1.0000
   4.750   0.7673   0.01146   0.00430  -0.0494   0.3764   1.0000
   5.000   0.7930   0.01177   0.00457  -0.0491   0.3499   1.0000
   5.250   0.8184   0.01213   0.00490  -0.0488   0.3218   1.0000
   5.500   0.8435   0.01253   0.00526  -0.0484   0.2933   1.0000
   5.750   0.8681   0.01300   0.00565  -0.0480   0.2617   1.0000
   6.000   0.8917   0.01360   0.00611  -0.0476   0.2214   1.0000
   6.250   0.9135   0.01447   0.00668  -0.0470   0.1643   1.0000
   6.500   0.9350   0.01540   0.00736  -0.0465   0.1141   1.0000
   6.750   0.9562   0.01639   0.00810  -0.0458   0.0713   1.0000
   7.000   0.9774   0.01736   0.00892  -0.0452   0.0416   1.0000
   7.250   0.9978   0.01847   0.00993  -0.0443   0.0215   1.0000
   7.500   1.0187   0.01954   0.01106  -0.0434   0.0152   1.0000
   7.750   1.0396   0.02053   0.01223  -0.0425   0.0133   1.0000
   8.000   1.0601   0.02153   0.01339  -0.0415   0.0121   1.0000
   8.250   1.0798   0.02255   0.01454  -0.0406   0.0109   1.0000
   8.500   1.0963   0.02392   0.01601  -0.0394   0.0099   1.0000
   8.750   1.1144   0.02502   0.01728  -0.0383   0.0092   1.0000
   9.000   1.1301   0.02638   0.01880  -0.0370   0.0088   1.0000
   9.250   1.1446   0.02784   0.02042  -0.0355   0.0085   1.0000
   9.500   1.1578   0.02941   0.02215  -0.0339   0.0082   1.0000
   9.750   1.1699   0.03107   0.02401  -0.0323   0.0080   1.0000
  10.000   1.1806   0.03284   0.02594  -0.0307   0.0078   1.0000
  10.250   1.1891   0.03470   0.02797  -0.0288   0.0076   1.0000
  10.500   1.1948   0.03661   0.03007  -0.0267   0.0075   1.0000
  10.750   1.1983   0.03872   0.03236  -0.0246   0.0074   1.0000
  11.000   1.1996   0.04103   0.03488  -0.0227   0.0073   1.0000
  11.250   1.1990   0.04359   0.03764  -0.0212   0.0073   1.0000
  11.500   1.1963   0.04646   0.04074  -0.0201   0.0072   1.0000
  11.750   1.1916   0.04971   0.04422  -0.0196   0.0072   1.0000
  12.000   1.1849   0.05338   0.04812  -0.0197   0.0072   1.0000
  12.250   1.1762   0.05755   0.05251  -0.0205   0.0071   1.0000
  12.500   1.1657   0.06229   0.05749  -0.0221   0.0071   1.0000
  12.750   1.1534   0.06762   0.06305  -0.0244   0.0072   1.0000
  13.000   1.1393   0.07366   0.06932  -0.0276   0.0072   1.0000
  13.250   1.1233   0.08045   0.07633  -0.0315   0.0072   1.0000
  13.500   1.1059   0.08799   0.08408  -0.0361   0.0073   1.0000
  13.750   1.0860   0.09658   0.09288  -0.0415   0.0073   1.0000
  14.000   1.0648   0.10622   0.10271  -0.0477   0.0074   1.0000
  14.250   1.0414   0.11736   0.11402  -0.0549   0.0075   1.0000
  14.500   1.0107   0.13191   0.12875  -0.0639   0.0078   1.0000
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