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SD7080 (9.2%) (sd7080-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD7080 (9.2%) (sd7080-il)
Reynolds number: 50,000
Max Cl/Cd: 33.63 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7080-il-50000.txt
Download as CSV file: xf-sd7080-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7080 (9.2%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3953   0.09732   0.09057  -0.0155   1.0000   0.2632
  -7.750  -0.4147   0.09677   0.09018  -0.0158   1.0000   0.2739
  -7.500  -0.4095   0.09370   0.08718  -0.0144   1.0000   0.2885
  -7.250  -0.4053   0.09074   0.08428  -0.0128   1.0000   0.3030
  -7.000  -0.4033   0.08795   0.08158  -0.0110   1.0000   0.3176
  -6.750  -0.4011   0.08523   0.07894  -0.0091   1.0000   0.3321
  -6.500  -0.4016   0.08271   0.07652  -0.0069   1.0000   0.3466
  -6.250  -0.4119   0.08091   0.07485  -0.0047   1.0000   0.3626
  -5.750  -0.3975   0.07470   0.06875   0.0005   1.0000   0.3970
  -5.500  -0.3952   0.07226   0.06638   0.0032   1.0000   0.4152
  -5.000  -0.4051   0.04984   0.04284  -0.0382   1.0000   0.1523
  -4.750  -0.3837   0.04333   0.03537  -0.0414   1.0000   0.1288
  -4.500  -0.3639   0.03989   0.03165  -0.0411   1.0000   0.1237
  -4.250  -0.3419   0.03637   0.02762  -0.0411   1.0000   0.1194
  -4.000  -0.3180   0.03338   0.02405  -0.0409   1.0000   0.1173
  -3.750  -0.2950   0.03126   0.02160  -0.0403   1.0000   0.1211
  -3.500  -0.2700   0.02926   0.01906  -0.0397   1.0000   0.1258
  -3.250  -0.2453   0.02731   0.01685  -0.0389   1.0000   0.1305
  -3.000  -0.2206   0.02574   0.01509  -0.0379   1.0000   0.1395
  -2.750  -0.1965   0.02430   0.01365  -0.0370   1.0000   0.1595
  -2.500  -0.1719   0.02281   0.01226  -0.0359   1.0000   0.2011
  -2.250  -0.1476   0.01999   0.01100  -0.0351   1.0000   0.4133
  -2.000  -0.1266   0.01760   0.01067  -0.0285   1.0000   1.0000
  -1.750  -0.1047   0.01767   0.01010  -0.0286   1.0000   1.0000
  -1.500  -0.0836   0.01782   0.00978  -0.0283   1.0000   1.0000
  -1.250  -0.0629   0.01803   0.00960  -0.0280   1.0000   1.0000
  -1.000  -0.0424   0.01829   0.00954  -0.0276   1.0000   1.0000
  -0.750  -0.0223   0.01861   0.00958  -0.0273   1.0000   1.0000
  -0.500  -0.0025   0.01897   0.00971  -0.0269   1.0000   1.0000
  -0.250   0.0168   0.01940   0.00991  -0.0266   1.0000   1.0000
   0.000   0.0358   0.01988   0.01020  -0.0264   1.0000   1.0000
   0.250   0.0542   0.02042   0.01059  -0.0262   1.0000   1.0000
   0.500   0.0723   0.02103   0.01107  -0.0260   1.0000   1.0000
   0.750   0.0898   0.02171   0.01161  -0.0259   1.0000   1.0000
   1.000   0.1108   0.02253   0.01233  -0.0267   0.9980   1.0000
   1.250   0.1712   0.02401   0.01369  -0.0344   0.9768   1.0000
   1.500   0.2295   0.02528   0.01487  -0.0414   0.9553   1.0000
   1.750   0.2811   0.02624   0.01580  -0.0468   0.9326   1.0000
   2.000   0.3320   0.02704   0.01659  -0.0517   0.9100   1.0000
   2.250   0.3829   0.02761   0.01719  -0.0561   0.8872   1.0000
   2.500   0.4269   0.02803   0.01766  -0.0591   0.8638   1.0000
   2.750   0.4825   0.02810   0.01784  -0.0633   0.8423   1.0000
   3.000   0.5241   0.02818   0.01800  -0.0651   0.8180   1.0000
   3.250   0.5817   0.02760   0.01759  -0.0683   0.7980   1.0000
   3.500   0.6169   0.02744   0.01753  -0.0683   0.7732   1.0000
   3.750   0.6584   0.02693   0.01713  -0.0686   0.7501   1.0000
   4.000   0.7001   0.02624   0.01657  -0.0685   0.7268   1.0000
   4.250   0.7322   0.02598   0.01639  -0.0673   0.7005   1.0000
   4.500   0.7641   0.02573   0.01620  -0.0660   0.6737   1.0000
   4.750   0.7944   0.02562   0.01615  -0.0646   0.6461   1.0000
   5.000   0.8226   0.02568   0.01622  -0.0629   0.6176   1.0000
   5.250   0.8490   0.02592   0.01645  -0.0612   0.5884   1.0000
   5.500   0.8743   0.02630   0.01682  -0.0596   0.5592   1.0000
   5.750   0.8987   0.02681   0.01735  -0.0579   0.5299   1.0000
   6.000   0.9224   0.02743   0.01794  -0.0562   0.5009   1.0000
   6.250   0.9457   0.02812   0.01862  -0.0546   0.4723   1.0000
   6.500   0.9688   0.02891   0.01938  -0.0531   0.4444   1.0000
   6.750   0.9919   0.02974   0.02019  -0.0515   0.4169   1.0000
   7.000   1.0133   0.03074   0.02120  -0.0500   0.3898   1.0000
   7.250   1.0330   0.03192   0.02248  -0.0484   0.3634   1.0000
   7.500   1.0529   0.03315   0.02376  -0.0468   0.3379   1.0000
   7.750   1.0745   0.03437   0.02497  -0.0453   0.3137   1.0000
   8.000   1.0935   0.03572   0.02640  -0.0437   0.2895   1.0000
   8.250   1.1105   0.03737   0.02817  -0.0420   0.2670   1.0000
   8.500   1.1316   0.03875   0.02946  -0.0406   0.2448   1.0000
   8.750   1.1443   0.04079   0.03178  -0.0386   0.2247   1.0000
   9.000   1.1599   0.04284   0.03400  -0.0368   0.2059   1.0000
   9.250   1.1789   0.04471   0.03576  -0.0354   0.1867   1.0000
   9.500   1.1882   0.04746   0.03880  -0.0332   0.1716   1.0000
   9.750   1.1956   0.05019   0.04178  -0.0310   0.1570   1.0000
  10.000   1.2018   0.05297   0.04475  -0.0288   0.1433   1.0000
  10.250   1.2074   0.05572   0.04763  -0.0267   0.1304   1.0000
  10.500   1.2138   0.05836   0.05031  -0.0248   0.1180   1.0000
  10.750   1.1952   0.06287   0.05540  -0.0218   0.1159   1.0000
  11.000   1.1742   0.06748   0.06040  -0.0194   0.1146   1.0000
  11.250   1.1492   0.07201   0.06519  -0.0172   0.1147   1.0000
  11.500   1.1227   0.07717   0.07053  -0.0164   0.1158   1.0000
  11.750   1.0970   0.08308   0.07657  -0.0172   0.1170   1.0000
  12.000   1.0722   0.08986   0.08344  -0.0194   0.1180   1.0000
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