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SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SD7003-085-88 (sd7003-il)
Reynolds number: 1,000,000
Max Cl/Cd: 93.74 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7003-il-1000000.txt
Download as CSV file: xf-sd7003-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7003-085-88                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.8808   0.04117   0.03903  -0.0436   1.0000   0.0064
 -11.000  -0.9022   0.03646   0.03407  -0.0442   1.0000   0.0063
 -10.750  -0.9072   0.03242   0.02971  -0.0443   1.0000   0.0064
 -10.500  -0.9040   0.02901   0.02598  -0.0439   1.0000   0.0065
 -10.250  -0.8942   0.02628   0.02296  -0.0432   1.0000   0.0065
 -10.000  -0.8783   0.02442   0.02087  -0.0426   1.0000   0.0067
  -9.750  -0.8602   0.02287   0.01912  -0.0420   1.0000   0.0068
  -9.500  -0.8404   0.02159   0.01766  -0.0413   1.0000   0.0069
  -9.250  -0.8250   0.01918   0.01492  -0.0404   1.0000   0.0072
  -9.000  -0.8068   0.01736   0.01288  -0.0395   1.0000   0.0074
  -8.750  -0.7853   0.01630   0.01171  -0.0388   1.0000   0.0077
  -8.500  -0.7623   0.01557   0.01090  -0.0382   1.0000   0.0080
  -8.250  -0.7392   0.01487   0.01011  -0.0375   1.0000   0.0082
  -8.000  -0.7157   0.01420   0.00936  -0.0368   1.0000   0.0085
  -7.750  -0.6922   0.01354   0.00860  -0.0361   1.0000   0.0088
  -7.500  -0.6684   0.01292   0.00790  -0.0354   1.0000   0.0091
  -7.250  -0.6444   0.01236   0.00728  -0.0347   1.0000   0.0094
  -7.000  -0.6200   0.01193   0.00678  -0.0340   1.0000   0.0097
  -6.750  -0.5971   0.01101   0.00577  -0.0332   1.0000   0.0107
  -6.500  -0.5725   0.01065   0.00539  -0.0325   1.0000   0.0116
  -6.250  -0.5479   0.01032   0.00502  -0.0318   1.0000   0.0126
  -6.000  -0.5237   0.00981   0.00445  -0.0311   1.0000   0.0141
  -5.750  -0.4996   0.00945   0.00410  -0.0303   1.0000   0.0161
  -5.500  -0.4753   0.00909   0.00370  -0.0295   1.0000   0.0188
  -5.250  -0.4508   0.00882   0.00344  -0.0288   1.0000   0.0221
  -5.000  -0.4167   0.00849   0.00314  -0.0302   0.9983   0.0271
  -4.750  -0.3800   0.00822   0.00289  -0.0321   0.9958   0.0330
  -4.500  -0.3435   0.00803   0.00271  -0.0339   0.9933   0.0389
  -4.250  -0.3084   0.00776   0.00249  -0.0354   0.9895   0.0475
  -4.000  -0.2716   0.00752   0.00230  -0.0373   0.9858   0.0568
  -3.750  -0.2341   0.00731   0.00212  -0.0393   0.9824   0.0665
  -3.500  -0.2015   0.00710   0.00194  -0.0401   0.9739   0.0765
  -3.250  -0.1682   0.00687   0.00176  -0.0412   0.9632   0.0913
  -3.000  -0.1354   0.00663   0.00160  -0.0421   0.9475   0.1135
  -2.750  -0.1053   0.00641   0.00143  -0.0424   0.9238   0.1432
  -2.500  -0.0788   0.00621   0.00129  -0.0419   0.8936   0.1827
  -2.250  -0.0530   0.00606   0.00118  -0.0413   0.8624   0.2254
  -2.000  -0.0269   0.00593   0.00109  -0.0408   0.8321   0.2713
  -1.750  -0.0007   0.00580   0.00101  -0.0403   0.8023   0.3239
  -1.500   0.0258   0.00568   0.00095  -0.0400   0.7732   0.3760
  -1.250   0.0523   0.00555   0.00089  -0.0396   0.7452   0.4378
  -1.000   0.0789   0.00540   0.00086  -0.0393   0.7180   0.5062
  -0.750   0.1057   0.00530   0.00084  -0.0390   0.6906   0.5664
  -0.500   0.1325   0.00521   0.00084  -0.0387   0.6638   0.6301
  -0.250   0.1592   0.00514   0.00085  -0.0383   0.6378   0.6888
   0.000   0.1859   0.00513   0.00087  -0.0379   0.6115   0.7351
   0.250   0.2124   0.00513   0.00090  -0.0374   0.5853   0.7748
   0.500   0.2391   0.00516   0.00093  -0.0370   0.5596   0.8090
   0.750   0.2653   0.00519   0.00097  -0.0364   0.5340   0.8402
   1.000   0.2911   0.00524   0.00101  -0.0357   0.5095   0.8704
   1.250   0.3161   0.00529   0.00106  -0.0349   0.4853   0.9007
   1.500   0.3403   0.00534   0.00110  -0.0338   0.4620   0.9318
   1.750   0.3681   0.00542   0.00113  -0.0335   0.4381   0.9643
   2.000   0.4053   0.00555   0.00116  -0.0355   0.4109   0.9923
   2.250   0.4350   0.00570   0.00121  -0.0358   0.3879   1.0000
   2.500   0.4621   0.00588   0.00129  -0.0357   0.3646   1.0000
   2.750   0.4895   0.00604   0.00136  -0.0355   0.3438   1.0000
   3.250   0.5441   0.00641   0.00156  -0.0352   0.3007   1.0000
   3.500   0.5714   0.00660   0.00166  -0.0350   0.2814   1.0000
   3.750   0.5986   0.00681   0.00178  -0.0349   0.2609   1.0000
   4.000   0.6258   0.00701   0.00192  -0.0347   0.2422   1.0000
   4.250   0.6529   0.00724   0.00206  -0.0346   0.2225   1.0000
   4.500   0.6800   0.00747   0.00222  -0.0344   0.2056   1.0000
   4.750   0.7071   0.00770   0.00239  -0.0342   0.1890   1.0000
   5.000   0.7341   0.00793   0.00256  -0.0341   0.1742   1.0000
   5.250   0.7611   0.00816   0.00275  -0.0339   0.1601   1.0000
   5.500   0.7879   0.00842   0.00295  -0.0337   0.1458   1.0000
   5.750   0.8146   0.00869   0.00317  -0.0335   0.1319   1.0000
   6.000   0.8411   0.00899   0.00340  -0.0333   0.1162   1.0000
   6.250   0.8676   0.00929   0.00364  -0.0331   0.1036   1.0000
   6.500   0.8940   0.00959   0.00390  -0.0328   0.0932   1.0000
   7.000   0.9465   0.01022   0.00446  -0.0323   0.0741   1.0000
   7.250   0.9727   0.01054   0.00476  -0.0321   0.0653   1.0000
   7.500   0.9985   0.01090   0.00510  -0.0318   0.0569   1.0000
   7.750   1.0240   0.01130   0.00546  -0.0315   0.0486   1.0000
   8.000   1.0497   0.01167   0.00581  -0.0312   0.0422   1.0000
   8.250   1.0748   0.01210   0.00623  -0.0308   0.0349   1.0000
   8.500   1.0994   0.01263   0.00672  -0.0304   0.0274   1.0000
   8.750   1.1234   0.01322   0.00730  -0.0299   0.0216   1.0000
   9.000   1.1478   0.01374   0.00783  -0.0294   0.0189   1.0000
   9.250   1.1711   0.01444   0.00857  -0.0287   0.0166   1.0000
   9.500   1.1955   0.01490   0.00909  -0.0283   0.0156   1.0000
   9.750   1.2193   0.01543   0.00966  -0.0278   0.0146   1.0000
  10.000   1.2419   0.01611   0.01040  -0.0271   0.0135   1.0000
  10.250   1.2619   0.01715   0.01154  -0.0262   0.0124   1.0000
  10.500   1.2850   0.01769   0.01216  -0.0256   0.0121   1.0000
  10.750   1.3072   0.01830   0.01285  -0.0249   0.0116   1.0000
  11.000   1.3289   0.01895   0.01356  -0.0242   0.0111   1.0000
  11.250   1.3499   0.01964   0.01431  -0.0235   0.0105   1.0000
  11.500   1.3694   0.02047   0.01521  -0.0226   0.0100   1.0000
  11.750   1.3837   0.02181   0.01666  -0.0211   0.0094   1.0000
  12.000   1.3960   0.02325   0.01824  -0.0194   0.0090   1.0000
  12.250   1.4140   0.02401   0.01910  -0.0184   0.0088   1.0000
  12.500   1.4296   0.02493   0.02011  -0.0171   0.0086   1.0000
  12.750   1.4429   0.02597   0.02125  -0.0156   0.0083   1.0000
  13.000   1.4550   0.02697   0.02234  -0.0140   0.0080   1.0000
  13.250   1.4601   0.02809   0.02356  -0.0114   0.0078   1.0000
  13.500   1.4627   0.02933   0.02490  -0.0088   0.0076   1.0000
  13.750   1.4637   0.03079   0.02645  -0.0067   0.0074   1.0000
  14.000   1.4628   0.03261   0.02837  -0.0050   0.0073   1.0000
  14.250   1.4577   0.03509   0.03096  -0.0040   0.0072   1.0000
  14.500   1.4503   0.03823   0.03423  -0.0040   0.0070   1.0000
  14.750   1.4416   0.04206   0.03817  -0.0050   0.0069   1.0000
  15.000   1.4220   0.04794   0.04423  -0.0076   0.0067   1.0000
  15.250   1.4065   0.05392   0.05036  -0.0108   0.0067   1.0000
  15.500   1.3852   0.06124   0.05784  -0.0150   0.0066   1.0000
  15.750   1.3663   0.06847   0.06523  -0.0191   0.0066   1.0000
  16.000   1.3419   0.07689   0.07379  -0.0240   0.0066   1.0000
  16.250   1.3275   0.08374   0.08075  -0.0279   0.0067   1.0000
  16.500   1.3064   0.09197   0.08911  -0.0326   0.0067   1.0000
  16.750   1.2847   0.10059   0.09786  -0.0376   0.0067   1.0000
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