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SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD7032-099-88 (sd7032-il)
Reynolds number: 50,000
Max Cl/Cd: 31.95 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7032-il-50000.txt
Download as CSV file: xf-sd7032-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3441   0.10755   0.10109  -0.0284   1.0000   0.2098
  -8.000  -0.3170   0.10163   0.09514  -0.0263   1.0000   0.2204
  -7.750  -0.3474   0.10265   0.09640  -0.0259   1.0000   0.2247
  -7.500  -0.3236   0.09736   0.09110  -0.0240   1.0000   0.2364
  -7.250  -0.3337   0.09551   0.08939  -0.0224   1.0000   0.2425
  -7.000  -0.3390   0.09388   0.08786  -0.0201   1.0000   0.2524
  -6.750  -0.3384   0.09117   0.08524  -0.0178   1.0000   0.2608
  -6.500  -0.3661   0.09126   0.08552  -0.0147   1.0000   0.2685
  -6.250  -0.3611   0.08830   0.08263  -0.0119   1.0000   0.2809
  -6.000  -0.3651   0.08610   0.08053  -0.0092   1.0000   0.2928
  -5.750  -0.3746   0.08427   0.07881  -0.0068   1.0000   0.3047
  -5.500  -0.3793   0.08222   0.07686  -0.0039   1.0000   0.3208
  -5.250  -0.3854   0.08030   0.07504  -0.0015   1.0000   0.3351
  -5.000  -0.3890   0.07828   0.07310   0.0014   1.0000   0.3539
  -4.750  -0.4064   0.07723   0.07217   0.0020   1.0000   0.3750
  -4.500  -0.3976   0.07410   0.06907   0.0072   1.0000   0.3942
  -3.750  -0.2889   0.04666   0.03971  -0.0487   1.0000   0.1493
  -3.500  -0.2562   0.04171   0.03418  -0.0519   1.0000   0.1327
  -3.250  -0.2271   0.03839   0.03036  -0.0537   1.0000   0.1299
  -3.000  -0.1974   0.03562   0.02704  -0.0551   1.0000   0.1298
  -2.750  -0.1683   0.03324   0.02413  -0.0559   1.0000   0.1295
  -2.500  -0.1407   0.03143   0.02182  -0.0562   1.0000   0.1328
  -2.250  -0.1162   0.03005   0.02023  -0.0561   1.0000   0.1417
  -2.000  -0.0912   0.02895   0.01874  -0.0557   1.0000   0.1503
  -1.750  -0.0686   0.02799   0.01773  -0.0551   1.0000   0.1663
  -1.500  -0.0457   0.02713   0.01693  -0.0545   1.0000   0.1931
  -1.250  -0.0176   0.02581   0.01611  -0.0548   1.0000   0.2793
  -1.000  -0.0147   0.02236   0.01566  -0.0477   1.0000   1.0000
  -0.750   0.0087   0.02296   0.01552  -0.0482   1.0000   1.0000
  -0.500   0.0298   0.02363   0.01572  -0.0486   1.0000   1.0000
  -0.250   0.0713   0.02478   0.01638  -0.0527   0.9900   1.0000
   0.000   0.1222   0.02608   0.01725  -0.0583   0.9744   1.0000
   0.250   0.1721   0.02731   0.01810  -0.0636   0.9585   1.0000
   0.500   0.2204   0.02844   0.01894  -0.0684   0.9426   1.0000
   0.750   0.2598   0.02933   0.01961  -0.0715   0.9256   1.0000
   1.000   0.2990   0.03018   0.02029  -0.0744   0.9083   1.0000
   1.250   0.3384   0.03099   0.02094  -0.0772   0.8911   1.0000
   1.500   0.3780   0.03174   0.02156  -0.0798   0.8743   1.0000
   1.750   0.4185   0.03241   0.02213  -0.0823   0.8578   1.0000
   2.000   0.4598   0.03297   0.02262  -0.0848   0.8415   1.0000
   2.250   0.5013   0.03343   0.02304  -0.0870   0.8257   1.0000
   2.500   0.5290   0.03405   0.02362  -0.0873   0.8075   1.0000
   2.750   0.5622   0.03453   0.02410  -0.0882   0.7903   1.0000
   3.000   0.5983   0.03488   0.02445  -0.0893   0.7738   1.0000
   3.250   0.6364   0.03507   0.02467  -0.0904   0.7576   1.0000
   3.500   0.6761   0.03510   0.02476  -0.0914   0.7420   1.0000
   3.750   0.7146   0.03500   0.02470  -0.0920   0.7266   1.0000
   4.000   0.7523   0.03479   0.02456  -0.0922   0.7112   1.0000
   4.250   0.7897   0.03450   0.02436  -0.0922   0.6958   1.0000
   4.500   0.8276   0.03408   0.02401  -0.0921   0.6804   1.0000
   4.750   0.8571   0.03414   0.02413  -0.0912   0.6631   1.0000
   5.000   0.8820   0.03449   0.02456  -0.0901   0.6446   1.0000
   5.250   0.9143   0.03433   0.02451  -0.0893   0.6274   1.0000
   5.500   0.9488   0.03399   0.02425  -0.0885   0.6103   1.0000
   5.750   0.9841   0.03359   0.02391  -0.0878   0.5933   1.0000
   6.000   1.0116   0.03382   0.02424  -0.0867   0.5749   1.0000
   6.250   1.0336   0.03449   0.02502  -0.0853   0.5555   1.0000
   6.500   1.0631   0.03460   0.02519  -0.0842   0.5369   1.0000
   6.750   1.0961   0.03452   0.02515  -0.0834   0.5188   1.0000
   7.000   1.1137   0.03563   0.02640  -0.0818   0.4992   1.0000
   7.250   1.1373   0.03629   0.02715  -0.0805   0.4798   1.0000
   7.500   1.1670   0.03653   0.02740  -0.0795   0.4610   1.0000
   7.750   1.1865   0.03755   0.02858  -0.0779   0.4417   1.0000
   8.000   1.2059   0.03857   0.02973  -0.0763   0.4222   1.0000
   8.250   1.2347   0.03885   0.02999  -0.0753   0.4023   1.0000
   8.500   1.2517   0.04009   0.03136  -0.0735   0.3831   1.0000
   8.750   1.2691   0.04121   0.03265  -0.0718   0.3634   1.0000
   9.000   1.2982   0.04146   0.03279  -0.0707   0.3422   1.0000
   9.250   1.3079   0.04318   0.03476  -0.0684   0.3232   1.0000
   9.500   1.3286   0.04394   0.03552  -0.0668   0.3019   1.0000
   9.750   1.3449   0.04525   0.03688  -0.0649   0.2821   1.0000
  10.000   1.3545   0.04696   0.03876  -0.0626   0.2633   1.0000
  10.250   1.3810   0.04768   0.03928  -0.0615   0.2416   1.0000
  10.500   1.3862   0.04991   0.04174  -0.0590   0.2259   1.0000
  10.750   1.3934   0.05228   0.04427  -0.0567   0.2113   1.0000
  11.000   1.4002   0.05452   0.04663  -0.0545   0.1974   1.0000
  11.250   1.4104   0.05694   0.04912  -0.0527   0.1845   1.0000
  11.500   1.3876   0.06119   0.05388  -0.0489   0.1805   1.0000
  11.750   1.3959   0.06361   0.05634  -0.0472   0.1695   1.0000
  12.000   1.3664   0.06799   0.06105  -0.0436   0.1682   1.0000
  12.250   1.3333   0.07317   0.06649  -0.0413   0.1681   1.0000
  12.500   1.2964   0.07962   0.07314  -0.0407   0.1692   1.0000
  12.750   1.2588   0.08741   0.08106  -0.0421   0.1707   1.0000
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