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SD7090 (10%) (sd7090-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SD7090 (10%) (sd7090-il)
Reynolds number: 50,000
Max Cl/Cd: 34.21 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7090-il-50000-n5.txt
Download as CSV file: xf-sd7090-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5031   0.10421   0.09672  -0.0262   1.0000   0.0552
 -10.000  -0.5048   0.09954   0.09211  -0.0281   1.0000   0.0552
  -9.750  -0.5087   0.09452   0.08716  -0.0306   1.0000   0.0552
  -9.500  -0.5135   0.08937   0.08207  -0.0333   1.0000   0.0552
  -9.250  -0.5222   0.08339   0.07615  -0.0371   1.0000   0.0551
  -9.000  -0.5322   0.07804   0.07085  -0.0402   1.0000   0.0549
  -8.750  -0.5465   0.07344   0.06629  -0.0417   1.0000   0.0547
  -8.500  -0.5597   0.06866   0.06145  -0.0430   1.0000   0.0547
  -8.250  -0.5703   0.06411   0.05677  -0.0435   1.0000   0.0547
  -8.000  -0.5792   0.05953   0.05197  -0.0436   1.0000   0.0549
  -7.750  -0.5833   0.05522   0.04737  -0.0430   1.0000   0.0551
  -7.250  -0.5765   0.04769   0.03927  -0.0410   1.0000   0.0559
  -7.000  -0.5671   0.04465   0.03597  -0.0398   1.0000   0.0568
  -6.750  -0.5555   0.04186   0.03292  -0.0385   1.0000   0.0580
  -6.500  -0.5416   0.03952   0.03034  -0.0372   1.0000   0.0600
  -6.250  -0.5269   0.03715   0.02759  -0.0359   1.0000   0.0634
  -6.000  -0.5105   0.03460   0.02448  -0.0345   1.0000   0.0666
  -5.750  -0.4923   0.03246   0.02211  -0.0332   1.0000   0.0691
  -5.500  -0.4730   0.03077   0.02030  -0.0320   1.0000   0.0724
  -5.250  -0.4529   0.02924   0.01845  -0.0307   1.0000   0.0783
  -5.000  -0.4330   0.02786   0.01701  -0.0294   1.0000   0.0848
  -4.750  -0.4120   0.02662   0.01552  -0.0281   1.0000   0.0935
  -4.500  -0.3922   0.02554   0.01449  -0.0269   1.0000   0.1040
  -4.250  -0.3720   0.02456   0.01349  -0.0256   1.0000   0.1177
  -4.000  -0.3515   0.02366   0.01254  -0.0244   1.0000   0.1344
  -3.750  -0.3309   0.02281   0.01172  -0.0232   1.0000   0.1540
  -3.500  -0.3097   0.02202   0.01098  -0.0223   1.0000   0.1801
  -3.250  -0.2898   0.02126   0.01037  -0.0212   1.0000   0.2123
  -3.000  -0.2705   0.02050   0.00986  -0.0202   1.0000   0.2613
  -2.750  -0.2516   0.01979   0.00951  -0.0190   1.0000   0.3338
  -2.500  -0.2343   0.01911   0.00934  -0.0174   1.0000   0.4331
  -2.250  -0.2194   0.01856   0.00937  -0.0149   1.0000   0.5543
  -2.000  -0.2063   0.01823   0.00951  -0.0114   1.0000   0.6817
  -1.750  -0.1725   0.01814   0.00973  -0.0110   0.9933   0.8303
  -1.500  -0.0877   0.01817   0.00956  -0.0212   0.9906   0.9945
  -1.250  -0.0423   0.01836   0.00943  -0.0256   0.9778   1.0000
  -1.000  -0.0002   0.01849   0.00930  -0.0291   0.9632   1.0000
  -0.750   0.0410   0.01860   0.00918  -0.0323   0.9483   1.0000
  -0.500   0.0820   0.01868   0.00907  -0.0353   0.9333   1.0000
  -0.250   0.1230   0.01873   0.00895  -0.0381   0.9183   1.0000
   0.000   0.1645   0.01873   0.00883  -0.0408   0.9033   1.0000
   0.250   0.2060   0.01870   0.00870  -0.0434   0.8881   1.0000
   0.500   0.2452   0.01866   0.00857  -0.0454   0.8721   1.0000
   0.750   0.2833   0.01861   0.00845  -0.0470   0.8556   1.0000
   1.000   0.3180   0.01859   0.00837  -0.0479   0.8373   1.0000
   1.250   0.3497   0.01860   0.00832  -0.0483   0.8175   1.0000
   1.500   0.3821   0.01860   0.00826  -0.0486   0.7978   1.0000
   1.750   0.4134   0.01861   0.00822  -0.0486   0.7779   1.0000
   2.000   0.4401   0.01871   0.00827  -0.0479   0.7555   1.0000
   2.250   0.4688   0.01877   0.00827  -0.0474   0.7344   1.0000
   2.500   0.4935   0.01893   0.00840  -0.0463   0.7110   1.0000
   2.750   0.5203   0.01907   0.00846  -0.0455   0.6888   1.0000
   3.000   0.5442   0.01928   0.00864  -0.0443   0.6645   1.0000
   3.250   0.5692   0.01948   0.00877  -0.0432   0.6410   1.0000
   3.500   0.5931   0.01972   0.00900  -0.0420   0.6163   1.0000
   3.750   0.6167   0.02000   0.00923  -0.0408   0.5917   1.0000
   4.000   0.6408   0.02028   0.00943  -0.0397   0.5678   1.0000
   4.250   0.6634   0.02062   0.00978  -0.0384   0.5423   1.0000
   4.500   0.6863   0.02098   0.01010  -0.0372   0.5175   1.0000
   4.750   0.7093   0.02137   0.01042  -0.0360   0.4935   1.0000
   5.000   0.7313   0.02181   0.01085  -0.0347   0.4682   1.0000
   5.250   0.7535   0.02228   0.01130  -0.0335   0.4442   1.0000
   5.500   0.7753   0.02278   0.01178  -0.0323   0.4202   1.0000
   5.750   0.7967   0.02333   0.01233  -0.0311   0.3964   1.0000
   6.000   0.8180   0.02391   0.01286  -0.0299   0.3741   1.0000
   6.250   0.8387   0.02455   0.01355  -0.0286   0.3513   1.0000
   6.500   0.8591   0.02521   0.01418  -0.0274   0.3298   1.0000
   6.750   0.8792   0.02594   0.01494  -0.0261   0.3088   1.0000
   7.000   0.8988   0.02670   0.01572  -0.0249   0.2884   1.0000
   7.250   0.9183   0.02751   0.01654  -0.0236   0.2700   1.0000
   7.500   0.9370   0.02838   0.01748  -0.0223   0.2510   1.0000
   7.750   0.9555   0.02932   0.01847  -0.0210   0.2335   1.0000
   8.000   0.9733   0.03029   0.01950  -0.0197   0.2169   1.0000
   8.250   0.9907   0.03134   0.02060  -0.0183   0.2016   1.0000
   8.500   1.0074   0.03245   0.02180  -0.0170   0.1871   1.0000
   8.750   1.0234   0.03364   0.02307  -0.0156   0.1735   1.0000
   9.000   1.0389   0.03492   0.02444  -0.0141   0.1612   1.0000
   9.250   1.0534   0.03624   0.02584  -0.0127   0.1498   1.0000
   9.500   1.0681   0.03758   0.02715  -0.0113   0.1401   1.0000
   9.750   1.0801   0.03917   0.02904  -0.0097   0.1299   1.0000
  10.000   1.0922   0.04086   0.03088  -0.0081   0.1215   1.0000
  10.250   1.1037   0.04242   0.03248  -0.0066   0.1141   1.0000
  10.500   1.1113   0.04447   0.03481  -0.0048   0.1070   1.0000
  10.750   1.1202   0.04618   0.03658  -0.0032   0.1013   1.0000
  11.000   1.1244   0.04850   0.03914  -0.0013   0.0965   1.0000
  11.250   1.1244   0.05088   0.04179   0.0007   0.0920   1.0000
  11.500   1.1302   0.05263   0.04356   0.0022   0.0877   1.0000
  11.750   1.1256   0.05568   0.04688   0.0038   0.0848   1.0000
  12.000   1.1144   0.05936   0.05091   0.0049   0.0826   1.0000
  12.250   1.1017   0.06331   0.05514   0.0053   0.0807   1.0000
  12.500   1.0880   0.06759   0.05963   0.0049   0.0789   1.0000
  12.750   1.0746   0.07212   0.06433   0.0038   0.0774   1.0000
  13.000   1.0830   0.07412   0.06623   0.0042   0.0743   1.0000
  13.250   1.0559   0.08105   0.07341   0.0010   0.0741   1.0000
  13.500   1.0270   0.08922   0.08177  -0.0035   0.0743   1.0000
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