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SD7090 (10%) (sd7090-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SD7090 (10%) (sd7090-il)
Reynolds number: 100,000
Max Cl/Cd: 47.11 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7090-il-100000.txt
Download as CSV file: xf-sd7090-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7090 (10%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4567   0.10006   0.09492  -0.0195   1.0000   0.1235
  -9.000  -0.4724   0.09690   0.09186  -0.0233   1.0000   0.1293
  -8.750  -0.5058   0.09343   0.08855  -0.0296   1.0000   0.1304
  -8.500  -0.4626   0.08959   0.08462  -0.0227   1.0000   0.1357
  -8.250  -0.4643   0.08649   0.08158  -0.0233   1.0000   0.1406
  -8.000  -0.5170   0.08256   0.07782  -0.0316   1.0000   0.1449
  -7.750  -0.4992   0.07865   0.07398  -0.0278   1.0000   0.1478
  -7.500  -0.4882   0.07603   0.07137  -0.0255   1.0000   0.1519
  -7.250  -0.5284   0.07100   0.06628  -0.0331   1.0000   0.1608
  -7.000  -0.5070   0.06790   0.06329  -0.0292   1.0000   0.1635
  -6.750  -0.5478   0.04850   0.04280  -0.0384   1.0000   0.0900
  -6.500  -0.5474   0.04131   0.03453  -0.0364   1.0000   0.0742
  -6.250  -0.5357   0.03732   0.03032  -0.0350   1.0000   0.0732
  -6.000  -0.5225   0.03442   0.02693  -0.0332   1.0000   0.0738
  -5.750  -0.5080   0.03146   0.02354  -0.0316   1.0000   0.0751
  -5.500  -0.4907   0.02881   0.02066  -0.0302   1.0000   0.0766
  -5.250  -0.4716   0.02679   0.01841  -0.0288   1.0000   0.0783
  -5.000  -0.4514   0.02511   0.01652  -0.0274   1.0000   0.0812
  -4.750  -0.4307   0.02387   0.01492  -0.0259   1.0000   0.0867
  -4.500  -0.4099   0.02224   0.01327  -0.0247   1.0000   0.0926
  -4.250  -0.3883   0.02111   0.01195  -0.0234   1.0000   0.1004
  -4.000  -0.3677   0.02002   0.01091  -0.0222   1.0000   0.1127
  -3.750  -0.3469   0.01909   0.00998  -0.0210   1.0000   0.1287
  -3.500  -0.3266   0.01825   0.00928  -0.0198   1.0000   0.1489
  -3.250  -0.3066   0.01765   0.00875  -0.0187   1.0000   0.1754
  -3.000  -0.2873   0.01693   0.00828  -0.0175   1.0000   0.2070
  -2.750  -0.2687   0.01618   0.00789  -0.0163   1.0000   0.2591
  -2.500  -0.2514   0.01523   0.00764  -0.0149   1.0000   0.3679
  -2.250  -0.2366   0.01440   0.00772  -0.0127   1.0000   0.5435
  -2.000  -0.2246   0.01407   0.00802  -0.0092   1.0000   0.7046
  -1.750  -0.2089   0.01400   0.00832  -0.0058   0.9998   0.8426
  -1.500  -0.1205   0.01424   0.00843  -0.0171   0.9964   1.0000
  -1.250  -0.0649   0.01461   0.00851  -0.0234   0.9852   1.0000
  -1.000  -0.0118   0.01486   0.00854  -0.0290   0.9732   1.0000
  -0.750   0.0396   0.01500   0.00850  -0.0340   0.9606   1.0000
  -0.500   0.0895   0.01506   0.00842  -0.0386   0.9475   1.0000
  -0.250   0.1393   0.01503   0.00828  -0.0430   0.9344   1.0000
   0.000   0.1906   0.01492   0.00808  -0.0475   0.9217   1.0000
   0.250   0.2472   0.01467   0.00777  -0.0527   0.9108   1.0000
   0.500   0.3023   0.01430   0.00736  -0.0574   0.8991   1.0000
   0.750   0.3449   0.01402   0.00704  -0.0597   0.8825   1.0000
   1.000   0.3820   0.01380   0.00678  -0.0608   0.8634   1.0000
   1.250   0.4175   0.01359   0.00653  -0.0615   0.8435   1.0000
   1.500   0.4512   0.01343   0.00630  -0.0617   0.8234   1.0000
   1.750   0.4755   0.01345   0.00626  -0.0603   0.7988   1.0000
   2.000   0.5019   0.01346   0.00617  -0.0593   0.7760   1.0000
   2.250   0.5250   0.01356   0.00620  -0.0577   0.7509   1.0000
   2.500   0.5480   0.01369   0.00623  -0.0561   0.7261   1.0000
   2.750   0.5718   0.01383   0.00625  -0.0546   0.7020   1.0000
   3.000   0.5936   0.01402   0.00636  -0.0529   0.6757   1.0000
   3.250   0.6160   0.01422   0.00648  -0.0513   0.6499   1.0000
   3.500   0.6390   0.01444   0.00657  -0.0499   0.6248   1.0000
   3.750   0.6609   0.01469   0.00674  -0.0483   0.5978   1.0000
   4.000   0.6830   0.01497   0.00695  -0.0468   0.5711   1.0000
   4.250   0.7053   0.01528   0.00715  -0.0454   0.5448   1.0000
   4.500   0.7277   0.01562   0.00735  -0.0440   0.5190   1.0000
   4.750   0.7494   0.01599   0.00765  -0.0426   0.4917   1.0000
   5.000   0.7711   0.01639   0.00799  -0.0412   0.4649   1.0000
   5.250   0.7929   0.01683   0.00833  -0.0398   0.4391   1.0000
   5.500   0.8147   0.01730   0.00867  -0.0385   0.4139   1.0000
   5.750   0.8358   0.01780   0.00913  -0.0372   0.3879   1.0000
   6.000   0.8571   0.01834   0.00961  -0.0359   0.3632   1.0000
   6.250   0.8784   0.01893   0.01009  -0.0346   0.3397   1.0000
   6.500   0.8990   0.01954   0.01068  -0.0333   0.3158   1.0000
   6.750   0.9201   0.02021   0.01123  -0.0321   0.2944   1.0000
   7.000   0.9403   0.02090   0.01195  -0.0308   0.2724   1.0000
   7.250   0.9608   0.02163   0.01262  -0.0295   0.2524   1.0000
   7.500   0.9812   0.02247   0.01335  -0.0284   0.2338   1.0000
   7.750   1.0007   0.02330   0.01425  -0.0270   0.2152   1.0000
   8.000   1.0201   0.02419   0.01517  -0.0257   0.1980   1.0000
   8.250   1.0394   0.02515   0.01612  -0.0244   0.1821   1.0000
   8.500   1.0584   0.02618   0.01716  -0.0231   0.1674   1.0000
   8.750   1.0772   0.02732   0.01834  -0.0218   0.1540   1.0000
   9.000   1.0957   0.02855   0.01964  -0.0206   0.1417   1.0000
   9.250   1.1147   0.02994   0.02102  -0.0194   0.1309   1.0000
   9.500   1.1351   0.03141   0.02237  -0.0186   0.1208   1.0000
   9.750   1.1492   0.03276   0.02407  -0.0166   0.1121   1.0000
  10.000   1.1678   0.03463   0.02597  -0.0156   0.1048   1.0000
  10.250   1.1821   0.03609   0.02766  -0.0139   0.0977   1.0000
  10.500   1.1984   0.03838   0.03005  -0.0128   0.0922   1.0000
  10.750   1.2082   0.04033   0.03236  -0.0106   0.0870   1.0000
  11.000   1.2278   0.04277   0.03461  -0.0104   0.0815   1.0000
  11.250   1.2266   0.04514   0.03756  -0.0071   0.0789   1.0000
  11.500   1.2263   0.04772   0.04054  -0.0044   0.0759   1.0000
  11.750   1.2328   0.04966   0.04258  -0.0025   0.0724   1.0000
  12.000   1.2413   0.05309   0.04600  -0.0016   0.0692   1.0000
  12.250   1.2238   0.05589   0.04921   0.0023   0.0685   1.0000
  12.500   1.2028   0.05910   0.05275   0.0056   0.0680   1.0000
  12.750   1.1801   0.06286   0.05680   0.0076   0.0677   1.0000
  13.000   1.1548   0.06730   0.06150   0.0081   0.0676   1.0000
  13.250   1.1281   0.07265   0.06708   0.0072   0.0678   1.0000
  13.500   1.0999   0.07898   0.07361   0.0047   0.0682   1.0000
  13.750   1.0719   0.08627   0.08105   0.0011   0.0688   1.0000
  14.000   1.0432   0.09469   0.08959  -0.0036   0.0694   1.0000
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