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SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD2030-086-88 (sd2030-il)
Reynolds number: 50,000
Max Cl/Cd: 37.59 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd2030-il-50000.txt
Download as CSV file: xf-sd2030-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD2030-086-88                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.4314   0.09183   0.08523  -0.0160   1.0000   0.2924
  -7.250  -0.4568   0.09137   0.08496  -0.0138   1.0000   0.3035
  -7.000  -0.4599   0.08885   0.08253  -0.0114   1.0000   0.3180
  -6.750  -0.4336   0.08420   0.07785  -0.0093   1.0000   0.3384
  -6.500  -0.4377   0.08198   0.07570  -0.0062   1.0000   0.3570
  -6.250  -0.4576   0.08077   0.07465  -0.0029   1.0000   0.3756
  -6.000  -0.4450   0.07763   0.07154   0.0008   1.0000   0.4026
  -4.750  -0.4407   0.04869   0.04111  -0.0331   1.0000   0.1577
  -4.500  -0.4201   0.04415   0.03610  -0.0336   1.0000   0.1418
  -4.250  -0.3998   0.04057   0.03211  -0.0334   1.0000   0.1363
  -4.000  -0.3749   0.03726   0.02796  -0.0334   1.0000   0.1288
  -3.750  -0.3516   0.03439   0.02472  -0.0329   1.0000   0.1261
  -3.500  -0.3267   0.03191   0.02177  -0.0323   1.0000   0.1247
  -3.250  -0.3011   0.02981   0.01922  -0.0315   1.0000   0.1257
  -3.000  -0.2754   0.02807   0.01705  -0.0307   1.0000   0.1318
  -2.750  -0.2507   0.02665   0.01546  -0.0298   1.0000   0.1431
  -2.500  -0.2254   0.02513   0.01386  -0.0288   1.0000   0.1565
  -2.250  -0.2006   0.02376   0.01256  -0.0276   1.0000   0.1890
  -2.000  -0.1758   0.02174   0.01124  -0.0268   1.0000   0.2918
  -1.750  -0.1387   0.01842   0.01028  -0.0243   1.0000   1.0000
  -1.500  -0.1198   0.01850   0.00986  -0.0231   1.0000   1.0000
  -1.250  -0.1006   0.01863   0.00959  -0.0221   1.0000   1.0000
  -1.000  -0.0810   0.01879   0.00943  -0.0212   1.0000   1.0000
  -0.750  -0.0612   0.01898   0.00933  -0.0204   1.0000   1.0000
  -0.500  -0.0412   0.01920   0.00929  -0.0196   1.0000   1.0000
  -0.250  -0.0212   0.01946   0.00933  -0.0189   1.0000   1.0000
   0.000  -0.0011   0.01975   0.00943  -0.0183   1.0000   1.0000
   0.250   0.0189   0.02008   0.00958  -0.0177   1.0000   1.0000
   0.500   0.0388   0.02044   0.00980  -0.0171   1.0000   1.0000
   0.750   0.0586   0.02083   0.01006  -0.0166   1.0000   1.0000
   1.000   0.0782   0.02127   0.01039  -0.0161   1.0000   1.0000
   1.250   0.0976   0.02174   0.01078  -0.0157   1.0000   1.0000
   1.500   0.1167   0.02226   0.01123  -0.0153   1.0000   1.0000
   1.750   0.1355   0.02283   0.01174  -0.0149   1.0000   1.0000
   2.000   0.1539   0.02345   0.01233  -0.0146   1.0000   1.0000
   2.250   0.1720   0.02413   0.01300  -0.0143   1.0000   1.0000
   2.500   0.1895   0.02488   0.01374  -0.0141   1.0000   1.0000
   2.750   0.2065   0.02570   0.01457  -0.0140   1.0000   1.0000
   3.000   0.2369   0.02696   0.01588  -0.0165   0.9937   1.0000
   3.250   0.2998   0.02880   0.01783  -0.0249   0.9682   1.0000
   3.500   0.3598   0.03023   0.01943  -0.0321   0.9417   1.0000
   3.750   0.4171   0.03121   0.02060  -0.0382   0.9141   1.0000
   4.000   0.4706   0.03174   0.02135  -0.0429   0.8848   1.0000
   4.250   0.5236   0.03188   0.02178  -0.0467   0.8538   1.0000
   4.500   0.5809   0.03147   0.02168  -0.0503   0.8218   1.0000
   4.750   0.6514   0.02997   0.02065  -0.0543   0.7893   1.0000
   5.000   0.7124   0.02791   0.01900  -0.0556   0.7518   1.0000
   5.250   0.7741   0.02511   0.01663  -0.0555   0.7056   1.0000
   5.500   0.8185   0.02310   0.01472  -0.0532   0.6393   1.0000
   5.750   0.8487   0.02258   0.01385  -0.0499   0.5515   1.0000
   6.000   0.8686   0.02346   0.01414  -0.0466   0.4644   1.0000
   6.250   0.8863   0.02492   0.01511  -0.0439   0.3907   1.0000
   6.500   0.9056   0.02661   0.01636  -0.0419   0.3310   1.0000
   6.750   0.9272   0.02847   0.01795  -0.0404   0.2844   1.0000
   7.000   0.9485   0.03030   0.01965  -0.0391   0.2476   1.0000
   7.250   0.9724   0.03244   0.02179  -0.0381   0.2205   1.0000
   7.500   0.9944   0.03454   0.02395  -0.0370   0.1981   1.0000
   7.750   1.0167   0.03714   0.02679  -0.0359   0.1824   1.0000
   8.000   1.0352   0.03954   0.02942  -0.0344   0.1671   1.0000
   8.250   1.0540   0.04259   0.03273  -0.0330   0.1566   1.0000
   8.500   1.0721   0.04556   0.03581  -0.0317   0.1451   1.0000
   8.750   1.0766   0.04884   0.03980  -0.0286   0.1378   1.0000
   9.000   1.0897   0.05260   0.04371  -0.0270   0.1306   1.0000
   9.250   1.0846   0.05651   0.04833  -0.0237   0.1265   1.0000
   9.500   1.1014   0.06027   0.05199  -0.0228   0.1182   1.0000
   9.750   1.0900   0.06470   0.05696  -0.0196   0.1174   1.0000
  10.000   1.0747   0.06926   0.06195  -0.0168   0.1169   1.0000
  10.250   1.0580   0.07392   0.06689  -0.0145   0.1170   1.0000
  10.500   1.0396   0.07853   0.07169  -0.0126   0.1174   1.0000
  10.750   1.0199   0.08327   0.07656  -0.0111   0.1179   1.0000
  11.000   1.0045   0.08851   0.08188  -0.0107   0.1184   1.0000
  11.250   0.9064   0.10452   0.09793  -0.0230   0.1470   1.0000
  11.500   0.9078   0.11047   0.10390  -0.0240   0.1458   1.0000
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