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SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SD2030-086-88 (sd2030-il)
Reynolds number: 200,000
Max Cl/Cd: 68.92 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd2030-il-200000-n5.txt
Download as CSV file: xf-sd2030-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD2030-086-88                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4479   0.08769   0.08410  -0.0352   1.0000   0.0198
  -8.750  -0.4560   0.08360   0.08007  -0.0361   1.0000   0.0196
  -8.500  -0.4632   0.08047   0.07701  -0.0364   1.0000   0.0199
  -8.250  -0.5053   0.07202   0.06871  -0.0400   1.0000   0.0177
  -8.000  -0.5156   0.06769   0.06437  -0.0410   1.0000   0.0175
  -7.750  -0.5297   0.06319   0.05984  -0.0409   1.0000   0.0177
  -7.500  -0.5322   0.05790   0.05443  -0.0429   0.9982   0.0179
  -7.250  -0.5169   0.05135   0.04764  -0.0483   0.9936   0.0182
  -7.000  -0.5029   0.04343   0.03923  -0.0520   0.9879   0.0178
  -6.750  -0.4810   0.03827   0.03357  -0.0545   0.9840   0.0175
  -6.500  -0.4612   0.03422   0.02907  -0.0555   0.9794   0.0174
  -6.250  -0.4402   0.03018   0.02446  -0.0564   0.9750   0.0175
  -6.000  -0.4148   0.02657   0.02030  -0.0574   0.9720   0.0177
  -5.750  -0.3872   0.02388   0.01719  -0.0584   0.9695   0.0181
  -5.500  -0.3641   0.02218   0.01521  -0.0579   0.9647   0.0185
  -5.250  -0.3355   0.02092   0.01375  -0.0585   0.9614   0.0194
  -5.000  -0.3045   0.01994   0.01259  -0.0595   0.9590   0.0206
  -4.750  -0.2722   0.01880   0.01123  -0.0606   0.9572   0.0216
  -4.500  -0.2467   0.01773   0.01000  -0.0602   0.9527   0.0220
  -4.250  -0.2188   0.01679   0.00894  -0.0602   0.9488   0.0224
  -4.000  -0.1879   0.01595   0.00800  -0.0610   0.9460   0.0231
  -3.750  -0.1553   0.01523   0.00719  -0.0620   0.9439   0.0241
  -3.500  -0.1264   0.01463   0.00650  -0.0623   0.9403   0.0251
  -3.250  -0.1001   0.01409   0.00593  -0.0621   0.9352   0.0274
  -3.000  -0.0681   0.01369   0.00548  -0.0631   0.9322   0.0316
  -2.750  -0.0351   0.01323   0.00504  -0.0642   0.9298   0.0448
  -2.500  -0.0090   0.01278   0.00472  -0.0640   0.9246   0.0762
  -2.000   0.0496   0.01170   0.00425  -0.0651   0.9168   0.2372
  -1.750   0.0737   0.01080   0.00412  -0.0649   0.9117   0.4347
  -1.500   0.0936   0.00993   0.00411  -0.0632   0.9057   0.6582
  -1.250   0.1188   0.00959   0.00416  -0.0617   0.9021   0.7935
  -1.000   0.1409   0.00953   0.00420  -0.0597   0.8953   0.8610
  -0.750   0.1706   0.00946   0.00414  -0.0593   0.8904   0.9042
  -0.500   0.2076   0.00939   0.00402  -0.0606   0.8864   0.9340
  -0.250   0.2459   0.00935   0.00394  -0.0624   0.8793   0.9579
   0.000   0.2937   0.00924   0.00376  -0.0663   0.8744   0.9730
   0.250   0.3382   0.00915   0.00363  -0.0696   0.8661   0.9843
   0.500   0.3832   0.00901   0.00343  -0.0731   0.8580   0.9914
   0.750   0.4235   0.00890   0.00328  -0.0757   0.8470   0.9986
   1.000   0.4504   0.00884   0.00317  -0.0754   0.8339   1.0000
   1.250   0.4738   0.00880   0.00309  -0.0744   0.8200   1.0000
   1.500   0.4972   0.00878   0.00303  -0.0733   0.8050   1.0000
   1.750   0.5204   0.00878   0.00299  -0.0722   0.7884   1.0000
   2.000   0.5426   0.00882   0.00298  -0.0709   0.7694   1.0000
   2.250   0.5656   0.00886   0.00297  -0.0698   0.7483   1.0000
   2.500   0.5881   0.00893   0.00299  -0.0685   0.7232   1.0000
   2.750   0.6105   0.00904   0.00300  -0.0671   0.6931   1.0000
   3.000   0.6323   0.00920   0.00303  -0.0657   0.6557   1.0000
   3.250   0.6527   0.00947   0.00309  -0.0640   0.6082   1.0000
   3.500   0.6716   0.00984   0.00320  -0.0621   0.5530   1.0000
   3.750   0.6894   0.01032   0.00341  -0.0601   0.4943   1.0000
   4.000   0.7075   0.01083   0.00366  -0.0583   0.4383   1.0000
   4.250   0.7263   0.01135   0.00394  -0.0566   0.3866   1.0000
   4.500   0.7457   0.01187   0.00425  -0.0552   0.3397   1.0000
   4.750   0.7657   0.01240   0.00459  -0.0539   0.2968   1.0000
   5.000   0.7864   0.01291   0.00497  -0.0528   0.2584   1.0000
   5.250   0.8073   0.01342   0.00535  -0.0517   0.2252   1.0000
   5.500   0.8286   0.01394   0.00574  -0.0507   0.1946   1.0000
   5.750   0.8499   0.01446   0.00616  -0.0497   0.1667   1.0000
   6.000   0.8712   0.01500   0.00661  -0.0488   0.1428   1.0000
   6.250   0.8928   0.01553   0.00711  -0.0478   0.1216   1.0000
   6.500   0.9141   0.01609   0.00762  -0.0469   0.1042   1.0000
   6.750   0.9354   0.01665   0.00817  -0.0459   0.0911   1.0000
   7.000   0.9566   0.01722   0.00876  -0.0449   0.0801   1.0000
   7.250   0.9773   0.01783   0.00939  -0.0439   0.0709   1.0000
   7.500   0.9971   0.01853   0.01008  -0.0427   0.0632   1.0000
   7.750   1.0178   0.01914   0.01083  -0.0416   0.0578   1.0000
   8.000   1.0367   0.01990   0.01158  -0.0404   0.0512   1.0000
   8.250   1.0582   0.02040   0.01217  -0.0396   0.0441   1.0000
   8.500   1.0779   0.02105   0.01284  -0.0386   0.0373   1.0000
   8.750   1.0975   0.02171   0.01354  -0.0375   0.0313   1.0000
   9.000   1.1159   0.02249   0.01442  -0.0362   0.0269   1.0000
   9.250   1.1331   0.02336   0.01538  -0.0348   0.0219   1.0000
   9.500   1.1485   0.02440   0.01655  -0.0331   0.0181   1.0000
   9.750   1.1621   0.02548   0.01769  -0.0312   0.0155   1.0000
  10.000   1.1735   0.02667   0.01901  -0.0289   0.0137   1.0000
  10.250   1.1861   0.02772   0.02019  -0.0269   0.0121   1.0000
  10.500   1.1969   0.02889   0.02146  -0.0249   0.0111   1.0000
  10.750   1.2032   0.03041   0.02309  -0.0223   0.0104   1.0000
  11.000   1.2102   0.03190   0.02478  -0.0200   0.0100   1.0000
  11.250   1.2157   0.03356   0.02664  -0.0176   0.0095   1.0000
  11.500   1.2197   0.03537   0.02864  -0.0153   0.0092   1.0000
  11.750   1.2221   0.03734   0.03085  -0.0131   0.0089   1.0000
  12.000   1.2233   0.03945   0.03317  -0.0111   0.0087   1.0000
  12.250   1.2225   0.04181   0.03573  -0.0093   0.0084   1.0000
  12.500   1.2202   0.04438   0.03850  -0.0077   0.0083   1.0000
  12.750   1.2160   0.04725   0.04158  -0.0066   0.0081   1.0000
  13.000   1.2096   0.05051   0.04504  -0.0058   0.0079   1.0000
  13.250   1.2013   0.05418   0.04892  -0.0056   0.0078   1.0000
  13.500   1.1916   0.05831   0.05326  -0.0061   0.0078   1.0000
  13.750   1.1798   0.06306   0.05823  -0.0073   0.0078   1.0000
  14.000   1.1654   0.06866   0.06405  -0.0095   0.0078   1.0000
  14.250   1.1486   0.07525   0.07086  -0.0128   0.0078   1.0000
  14.500   1.1305   0.08276   0.07859  -0.0171   0.0078   1.0000
  14.750   1.1095   0.09166   0.08771  -0.0226   0.0079   1.0000
  15.000   1.0848   0.10216   0.09842  -0.0293   0.0079   1.0000
  15.250   1.0550   0.11468   0.11114  -0.0370   0.0081   1.0000
  15.500   1.0136   0.13123   0.12785  -0.0467   0.0085   1.0000
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