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SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SD7003-085-88 (sd7003-il)
Reynolds number: 200,000
Max Cl/Cd: 57.96 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7003-il-200000-n5.txt
Download as CSV file: xf-sd7003-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6251   0.08127   0.07770  -0.0114   1.0000   0.0130
  -9.750  -0.6499   0.07141   0.06791  -0.0174   1.0000   0.0128
  -9.250  -0.7112   0.04793   0.04418  -0.0370   1.0000   0.0122
  -9.000  -0.7280   0.04039   0.03610  -0.0396   1.0000   0.0122
  -8.750  -0.7297   0.03471   0.02979  -0.0402   1.0000   0.0124
  -8.500  -0.7208   0.03066   0.02517  -0.0399   1.0000   0.0126
  -8.250  -0.7060   0.02765   0.02166  -0.0393   1.0000   0.0129
  -8.000  -0.6884   0.02543   0.01915  -0.0387   1.0000   0.0133
  -7.750  -0.6680   0.02394   0.01750  -0.0381   1.0000   0.0139
  -7.500  -0.6467   0.02258   0.01595  -0.0375   1.0000   0.0146
  -7.250  -0.6249   0.02122   0.01438  -0.0368   1.0000   0.0155
  -7.000  -0.6024   0.02001   0.01293  -0.0360   1.0000   0.0168
  -6.750  -0.5798   0.01906   0.01190  -0.0354   1.0000   0.0185
  -6.500  -0.5566   0.01824   0.01097  -0.0347   1.0000   0.0204
  -6.250  -0.5334   0.01724   0.00981  -0.0339   1.0000   0.0225
  -6.000  -0.5103   0.01643   0.00897  -0.0332   1.0000   0.0250
  -5.750  -0.4863   0.01587   0.00830  -0.0325   1.0000   0.0288
  -5.500  -0.4626   0.01524   0.00767  -0.0319   1.0000   0.0331
  -5.250  -0.4383   0.01478   0.00712  -0.0312   1.0000   0.0383
  -5.000  -0.4144   0.01427   0.00663  -0.0306   1.0000   0.0441
  -4.750  -0.3903   0.01378   0.00609  -0.0299   1.0000   0.0500
  -4.500  -0.3663   0.01333   0.00563  -0.0292   1.0000   0.0563
  -4.250  -0.3423   0.01291   0.00519  -0.0285   1.0000   0.0637
  -4.000  -0.3182   0.01258   0.00482  -0.0278   1.0000   0.0718
  -3.750  -0.2944   0.01220   0.00449  -0.0271   1.0000   0.0816
  -3.500  -0.2635   0.01186   0.00416  -0.0279   0.9965   0.0951
  -3.250  -0.2260   0.01150   0.00385  -0.0300   0.9887   0.1145
  -3.000  -0.1888   0.01112   0.00359  -0.0321   0.9802   0.1440
  -2.500  -0.1175   0.01031   0.00314  -0.0356   0.9577   0.2390
  -2.250  -0.0826   0.00992   0.00296  -0.0372   0.9435   0.3011
  -2.000  -0.0474   0.00952   0.00280  -0.0387   0.9273   0.3713
  -1.750  -0.0139   0.00912   0.00266  -0.0398   0.9071   0.4545
  -1.500   0.0181   0.00874   0.00258  -0.0404   0.8843   0.5443
  -1.250   0.0467   0.00845   0.00254  -0.0400   0.8581   0.6292
  -1.000   0.0730   0.00828   0.00251  -0.0390   0.8306   0.6986
  -0.750   0.0977   0.00820   0.00248  -0.0376   0.8025   0.7531
  -0.500   0.1216   0.00818   0.00246  -0.0361   0.7744   0.7981
  -0.250   0.1451   0.00818   0.00242  -0.0345   0.7470   0.8385
   0.250   0.1966   0.00826   0.00235  -0.0323   0.6914   0.9105
   0.500   0.2288   0.00832   0.00229  -0.0327   0.6623   0.9437
   0.750   0.2660   0.00842   0.00223  -0.0344   0.6318   0.9750
   1.000   0.3003   0.00854   0.00219  -0.0357   0.6021   1.0000
   1.250   0.3253   0.00871   0.00221  -0.0351   0.5747   1.0000
   1.500   0.3507   0.00889   0.00224  -0.0345   0.5479   1.0000
   1.750   0.3764   0.00908   0.00229  -0.0340   0.5216   1.0000
   2.000   0.4021   0.00929   0.00236  -0.0335   0.4957   1.0000
   2.250   0.4281   0.00950   0.00245  -0.0331   0.4701   1.0000
   2.500   0.4542   0.00972   0.00255  -0.0327   0.4446   1.0000
   2.750   0.4803   0.00995   0.00267  -0.0323   0.4199   1.0000
   3.000   0.5064   0.01020   0.00282  -0.0320   0.3954   1.0000
   3.250   0.5326   0.01044   0.00297  -0.0316   0.3714   1.0000
   3.500   0.5587   0.01071   0.00314  -0.0313   0.3484   1.0000
   3.750   0.5849   0.01098   0.00335  -0.0310   0.3254   1.0000
   4.000   0.6110   0.01128   0.00356  -0.0307   0.3039   1.0000
   4.250   0.6371   0.01157   0.00379  -0.0304   0.2826   1.0000
   4.750   0.6891   0.01222   0.00434  -0.0298   0.2434   1.0000
   5.000   0.7150   0.01256   0.00463  -0.0294   0.2248   1.0000
   5.250   0.7407   0.01293   0.00495  -0.0291   0.2071   1.0000
   5.500   0.7663   0.01332   0.00531  -0.0288   0.1904   1.0000
   5.750   0.7920   0.01370   0.00568  -0.0285   0.1748   1.0000
   6.000   0.8174   0.01411   0.00608  -0.0281   0.1600   1.0000
   6.250   0.8427   0.01454   0.00650  -0.0278   0.1462   1.0000
   6.500   0.8678   0.01500   0.00697  -0.0274   0.1333   1.0000
   7.000   0.9175   0.01596   0.00796  -0.0266   0.1100   1.0000
   7.250   0.9421   0.01648   0.00849  -0.0262   0.0987   1.0000
   7.500   0.9663   0.01702   0.00905  -0.0258   0.0872   1.0000
   7.750   0.9902   0.01761   0.00967  -0.0253   0.0763   1.0000
   8.000   1.0137   0.01824   0.01031  -0.0248   0.0668   1.0000
   8.250   1.0366   0.01895   0.01101  -0.0243   0.0580   1.0000
   8.500   1.0597   0.01960   0.01175  -0.0237   0.0501   1.0000
   8.750   1.0819   0.02038   0.01261  -0.0231   0.0436   1.0000
   9.000   1.1028   0.02131   0.01356  -0.0224   0.0379   1.0000
   9.250   1.1239   0.02219   0.01458  -0.0216   0.0336   1.0000
   9.500   1.1432   0.02325   0.01569  -0.0207   0.0300   1.0000
   9.750   1.1620   0.02433   0.01691  -0.0198   0.0272   1.0000
  10.000   1.1806   0.02537   0.01807  -0.0188   0.0248   1.0000
  10.250   1.1969   0.02661   0.01943  -0.0177   0.0231   1.0000
  10.500   1.2100   0.02812   0.02105  -0.0164   0.0220   1.0000
  10.750   1.2242   0.02948   0.02259  -0.0151   0.0210   1.0000
  11.000   1.2363   0.03093   0.02422  -0.0136   0.0201   1.0000
  11.250   1.2469   0.03241   0.02585  -0.0121   0.0192   1.0000
  11.500   1.2547   0.03390   0.02748  -0.0104   0.0184   1.0000
  11.750   1.2582   0.03546   0.02916  -0.0084   0.0178   1.0000
  12.000   1.2572   0.03744   0.03124  -0.0065   0.0172   1.0000
  12.250   1.2526   0.03998   0.03390  -0.0051   0.0168   1.0000
  12.500   1.2503   0.04259   0.03671  -0.0044   0.0165   1.0000
  12.750   1.2468   0.04562   0.03994  -0.0045   0.0162   1.0000
  13.000   1.2415   0.04915   0.04368  -0.0053   0.0160   1.0000
  13.250   1.2345   0.05325   0.04798  -0.0067   0.0158   1.0000
  13.500   1.2264   0.05782   0.05275  -0.0089   0.0156   1.0000
  13.750   1.2163   0.06303   0.05815  -0.0116   0.0155   1.0000
  14.000   1.2042   0.06886   0.06417  -0.0150   0.0153   1.0000
  14.250   1.1905   0.07527   0.07077  -0.0188   0.0152   1.0000
  14.500   1.1751   0.08228   0.07795  -0.0231   0.0151   1.0000
  14.750   1.1577   0.08993   0.08578  -0.0278   0.0151   1.0000
  15.000   1.1376   0.09846   0.09447  -0.0330   0.0151   1.0000
  15.250   1.1164   0.10772   0.10390  -0.0388   0.0152   1.0000
  15.500   1.0923   0.11814   0.11448  -0.0451   0.0154   1.0000
  15.750   1.0653   0.12994   0.12641  -0.0523   0.0156   1.0000
  16.000   1.0269   0.14577   0.14238  -0.0618   0.0160   1.0000
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