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SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SD7032-099-88 (sd7032-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.32 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7032-il-1000000.txt
Download as CSV file: xf-sd7032-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7032-099-88                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3279   0.09279   0.09120  -0.0378   1.0000   0.0102
  -9.000  -0.3286   0.08971   0.08814  -0.0381   1.0000   0.0102
  -8.500  -0.3290   0.07941   0.07789  -0.0446   0.9960   0.0104
  -8.250  -0.3175   0.07516   0.07366  -0.0493   0.9902   0.0105
  -8.000  -0.3013   0.07106   0.06956  -0.0550   0.9857   0.0107
  -7.750  -0.2841   0.06507   0.06357  -0.0641   0.9796   0.0108
  -7.500  -0.2607   0.05858   0.05705  -0.0762   0.9722   0.0111
  -7.250  -0.2441   0.05200   0.05040  -0.0865   0.9590   0.0116
  -7.000  -0.2760   0.02910   0.02667  -0.0977   0.9326   0.0094
  -6.750  -0.2741   0.01953   0.01608  -0.0981   0.9220   0.0089
  -6.500  -0.2539   0.01647   0.01252  -0.0976   0.9153   0.0090
  -6.250  -0.2301   0.01462   0.01035  -0.0972   0.9092   0.0091
  -6.000  -0.2046   0.01358   0.00911  -0.0969   0.9029   0.0095
  -5.750  -0.1783   0.01291   0.00828  -0.0966   0.8973   0.0099
  -5.500  -0.1513   0.01238   0.00762  -0.0964   0.8906   0.0102
  -5.250  -0.1267   0.01073   0.00576  -0.0960   0.8843   0.0109
  -5.000  -0.0994   0.01035   0.00535  -0.0959   0.8773   0.0116
  -4.750  -0.0721   0.01001   0.00494  -0.0956   0.8705   0.0124
  -4.500  -0.0445   0.00964   0.00450  -0.0955   0.8631   0.0132
  -4.250  -0.0169   0.00944   0.00422  -0.0953   0.8556   0.0137
  -4.000   0.0102   0.00869   0.00341  -0.0952   0.8473   0.0153
  -3.750   0.0379   0.00850   0.00317  -0.0951   0.8392   0.0169
  -3.500   0.0660   0.00841   0.00305  -0.0950   0.8299   0.0182
  -3.250   0.0936   0.00790   0.00246  -0.0949   0.8206   0.0209
  -3.000   0.1214   0.00772   0.00221  -0.0948   0.8108   0.0230
  -2.750   0.1495   0.00751   0.00193  -0.0947   0.7998   0.0255
  -2.500   0.1776   0.00732   0.00171  -0.0947   0.7886   0.0295
  -2.250   0.2056   0.00717   0.00151  -0.0946   0.7768   0.0360
  -2.000   0.2333   0.00686   0.00135  -0.0945   0.7642   0.0843
  -1.750   0.2610   0.00662   0.00124  -0.0946   0.7510   0.1454
  -1.500   0.2887   0.00639   0.00116  -0.0946   0.7372   0.2152
  -1.250   0.3163   0.00618   0.00111  -0.0947   0.7228   0.2903
  -1.000   0.3439   0.00597   0.00108  -0.0947   0.7081   0.3746
  -0.750   0.3713   0.00575   0.00107  -0.0947   0.6932   0.4732
  -0.500   0.3986   0.00556   0.00109  -0.0947   0.6780   0.5703
  -0.250   0.4260   0.00547   0.00111  -0.0945   0.6626   0.6381
   0.000   0.4530   0.00538   0.00115  -0.0943   0.6470   0.7079
   0.250   0.4795   0.00533   0.00120  -0.0939   0.6311   0.7693
   0.500   0.5058   0.00532   0.00125  -0.0934   0.6151   0.8145
   0.750   0.5317   0.00534   0.00129  -0.0928   0.5989   0.8545
   1.000   0.5558   0.00533   0.00133  -0.0918   0.5822   0.8989
   1.250   0.5826   0.00530   0.00133  -0.0913   0.5647   0.9715
   1.500   0.6134   0.00543   0.00136  -0.0920   0.5467   1.0000
   1.750   0.6411   0.00557   0.00142  -0.0919   0.5297   1.0000
   2.000   0.6687   0.00572   0.00147  -0.0919   0.5126   1.0000
   2.250   0.6962   0.00587   0.00154  -0.0918   0.4959   1.0000
   2.500   0.7236   0.00603   0.00162  -0.0918   0.4795   1.0000
   2.750   0.7509   0.00620   0.00171  -0.0917   0.4626   1.0000
   3.000   0.7782   0.00637   0.00180  -0.0916   0.4469   1.0000
   3.250   0.8053   0.00654   0.00190  -0.0915   0.4313   1.0000
   3.500   0.8324   0.00673   0.00202  -0.0914   0.4153   1.0000
   3.750   0.8594   0.00691   0.00213  -0.0913   0.4004   1.0000
   4.000   0.8864   0.00710   0.00226  -0.0911   0.3853   1.0000
   4.250   0.9132   0.00730   0.00239  -0.0910   0.3700   1.0000
   4.500   0.9399   0.00750   0.00255  -0.0909   0.3550   1.0000
   4.750   0.9664   0.00772   0.00270  -0.0907   0.3394   1.0000
   5.000   0.9929   0.00794   0.00286  -0.0905   0.3242   1.0000
   5.250   1.0191   0.00817   0.00304  -0.0903   0.3090   1.0000
   5.500   1.0453   0.00841   0.00323  -0.0901   0.2943   1.0000
   5.750   1.0712   0.00867   0.00342  -0.0898   0.2791   1.0000
   6.000   1.0969   0.00894   0.00363  -0.0896   0.2629   1.0000
   6.250   1.1222   0.00924   0.00387  -0.0892   0.2467   1.0000
   6.500   1.1477   0.00952   0.00410  -0.0889   0.2326   1.0000
   6.750   1.1729   0.00981   0.00434  -0.0886   0.2193   1.0000
   7.000   1.1977   0.01014   0.00462  -0.0882   0.2042   1.0000
   7.250   1.2224   0.01046   0.00490  -0.0878   0.1906   1.0000
   7.500   1.2468   0.01081   0.00519  -0.0874   0.1770   1.0000
   7.750   1.2708   0.01118   0.00551  -0.0869   0.1637   1.0000
   8.000   1.2947   0.01155   0.00585  -0.0864   0.1511   1.0000
   8.250   1.3180   0.01196   0.00620  -0.0858   0.1380   1.0000
   8.500   1.3409   0.01239   0.00658  -0.0851   0.1246   1.0000
   8.750   1.3632   0.01285   0.00699  -0.0844   0.1111   1.0000
   9.000   1.3847   0.01338   0.00744  -0.0836   0.0967   1.0000
   9.250   1.4045   0.01401   0.00798  -0.0825   0.0803   1.0000
   9.500   1.4244   0.01461   0.00852  -0.0815   0.0674   1.0000
   9.750   1.4438   0.01523   0.00908  -0.0803   0.0565   1.0000
  10.000   1.4631   0.01581   0.00963  -0.0792   0.0490   1.0000
  10.250   1.4826   0.01634   0.01017  -0.0781   0.0433   1.0000
  10.500   1.5000   0.01700   0.01080  -0.0766   0.0373   1.0000
  10.750   1.5186   0.01751   0.01134  -0.0754   0.0338   1.0000
  11.000   1.5330   0.01819   0.01201  -0.0735   0.0292   1.0000
  11.250   1.5479   0.01871   0.01258  -0.0716   0.0268   1.0000
  11.500   1.5600   0.01937   0.01325  -0.0694   0.0239   1.0000
  11.750   1.5713   0.02011   0.01401  -0.0671   0.0210   1.0000
  12.000   1.5833   0.02081   0.01475  -0.0650   0.0187   1.0000
  12.250   1.5921   0.02176   0.01571  -0.0627   0.0158   1.0000
  12.500   1.6025   0.02261   0.01661  -0.0607   0.0139   1.0000
  12.750   1.6093   0.02375   0.01778  -0.0584   0.0114   1.0000
  13.000   1.6159   0.02495   0.01901  -0.0562   0.0095   1.0000
  13.250   1.6209   0.02634   0.02046  -0.0541   0.0076   1.0000
  13.500   1.6240   0.02793   0.02211  -0.0520   0.0065   1.0000
  13.750   1.6268   0.02964   0.02391  -0.0501   0.0057   1.0000
  14.000   1.6310   0.03130   0.02566  -0.0486   0.0052   1.0000
  14.250   1.6333   0.03322   0.02766  -0.0471   0.0048   1.0000
  14.500   1.6326   0.03552   0.03005  -0.0458   0.0045   1.0000
  14.750   1.6276   0.03841   0.03306  -0.0446   0.0041   1.0000
  15.000   1.6292   0.04077   0.03553  -0.0439   0.0039   1.0000
  15.250   1.6281   0.04355   0.03843  -0.0435   0.0037   1.0000
  15.500   1.6258   0.04662   0.04161  -0.0433   0.0036   1.0000
  15.750   1.6227   0.04993   0.04503  -0.0435   0.0034   1.0000
  16.000   1.6175   0.05369   0.04891  -0.0440   0.0033   1.0000
  16.250   1.6120   0.05771   0.05304  -0.0448   0.0032   1.0000
  16.500   1.6029   0.06242   0.05788  -0.0460   0.0031   1.0000
  16.750   1.5926   0.06753   0.06312  -0.0476   0.0030   1.0000
  17.000   1.5787   0.07348   0.06920  -0.0498   0.0030   1.0000
  17.250   1.5647   0.07966   0.07552  -0.0523   0.0029   1.0000
  17.500   1.5487   0.08641   0.08242  -0.0552   0.0029   1.0000
  17.750   1.5341   0.09316   0.08930  -0.0582   0.0029   1.0000
  18.000   1.5124   0.10140   0.09769  -0.0622   0.0028   1.0000
  18.250   1.4950   0.10904   0.10548  -0.0660   0.0028   1.0000
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