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SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: SD2030-086-88 (sd2030-il)
Reynolds number: 1,000,000
Max Cl/Cd: 87.34 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd2030-il-1000000-n5.txt
Download as CSV file: xf-sd2030-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4785   0.09004   0.08839  -0.0335   1.0000   0.0063
  -9.750  -0.4873   0.08536   0.08373  -0.0347   1.0000   0.0065
  -9.250  -0.6152   0.03109   0.02864  -0.0768   0.9844   0.0070
  -9.000  -0.6039   0.02577   0.02278  -0.0783   0.9812   0.0072
  -8.750  -0.5859   0.02339   0.02011  -0.0782   0.9774   0.0073
  -8.500  -0.5640   0.02147   0.01793  -0.0785   0.9745   0.0074
  -8.250  -0.5400   0.01991   0.01614  -0.0788   0.9721   0.0075
  -8.000  -0.5147   0.01857   0.01458  -0.0792   0.9699   0.0076
  -7.750  -0.4936   0.01771   0.01357  -0.0783   0.9655   0.0076
  -7.500  -0.4763   0.01514   0.01063  -0.0773   0.9608   0.0081
  -7.250  -0.4510   0.01435   0.00974  -0.0771   0.9580   0.0084
  -7.000  -0.4262   0.01370   0.00900  -0.0768   0.9547   0.0086
  -6.750  -0.4023   0.01310   0.00831  -0.0762   0.9502   0.0088
  -6.500  -0.3771   0.01252   0.00765  -0.0758   0.9463   0.0090
  -6.250  -0.3510   0.01202   0.00706  -0.0756   0.9430   0.0094
  -6.000  -0.3262   0.01149   0.00646  -0.0751   0.9384   0.0096
  -5.750  -0.3008   0.01102   0.00592  -0.0747   0.9335   0.0100
  -5.500  -0.2747   0.01057   0.00538  -0.0744   0.9294   0.0102
  -5.250  -0.2491   0.01013   0.00488  -0.0740   0.9241   0.0105
  -5.000  -0.2233   0.00972   0.00439  -0.0736   0.9186   0.0107
  -4.750  -0.1969   0.00936   0.00397  -0.0733   0.9136   0.0109
  -4.500  -0.1707   0.00902   0.00359  -0.0730   0.9074   0.0111
  -4.250  -0.1441   0.00873   0.00324  -0.0728   0.9016   0.0113
  -4.000  -0.1173   0.00851   0.00298  -0.0725   0.8950   0.0115
  -3.750  -0.0905   0.00829   0.00271  -0.0723   0.8884   0.0117
  -3.500  -0.0638   0.00801   0.00237  -0.0721   0.8814   0.0119
  -3.250  -0.0372   0.00771   0.00198  -0.0717   0.8738   0.0128
  -3.000  -0.0102   0.00752   0.00175  -0.0715   0.8660   0.0139
  -2.750   0.0169   0.00738   0.00157  -0.0713   0.8583   0.0150
  -2.500   0.0441   0.00727   0.00142  -0.0711   0.8494   0.0160
  -2.250   0.0712   0.00718   0.00129  -0.0709   0.8398   0.0171
  -2.000   0.0982   0.00708   0.00117  -0.0707   0.8295   0.0228
  -1.750   0.1249   0.00692   0.00106  -0.0705   0.8188   0.0481
  -1.500   0.1515   0.00673   0.00098  -0.0703   0.8079   0.0838
  -1.250   0.1781   0.00656   0.00091  -0.0701   0.7967   0.1275
  -1.000   0.2045   0.00638   0.00085  -0.0699   0.7849   0.1811
  -0.750   0.2307   0.00618   0.00080  -0.0696   0.7716   0.2481
  -0.500   0.2569   0.00599   0.00077  -0.0694   0.7573   0.3158
  -0.250   0.2812   0.00548   0.00074  -0.0690   0.7420   0.4923
   0.000   0.3054   0.00509   0.00074  -0.0684   0.7241   0.6383
   0.250   0.3290   0.00487   0.00079  -0.0675   0.7028   0.7521
   0.500   0.3533   0.00487   0.00084  -0.0667   0.6757   0.8049
   0.750   0.3778   0.00495   0.00090  -0.0659   0.6457   0.8366
   1.000   0.4022   0.00509   0.00096  -0.0651   0.6124   0.8596
   1.250   0.4259   0.00528   0.00104  -0.0641   0.5728   0.8786
   1.500   0.4494   0.00549   0.00113  -0.0632   0.5324   0.8955
   1.750   0.4724   0.00575   0.00124  -0.0621   0.4867   0.9113
   2.000   0.4952   0.00600   0.00135  -0.0610   0.4441   0.9254
   2.250   0.5177   0.00626   0.00147  -0.0599   0.4013   0.9392
   2.500   0.5402   0.00655   0.00159  -0.0588   0.3563   0.9529
   2.750   0.5655   0.00679   0.00171  -0.0583   0.3226   0.9652
   3.000   0.5936   0.00706   0.00184  -0.0586   0.2867   0.9746
   3.500   0.6541   0.00764   0.00214  -0.0601   0.2221   0.9883
   4.000   0.7129   0.00818   0.00247  -0.0612   0.1730   1.0000
   4.250   0.7363   0.00847   0.00265  -0.0605   0.1488   1.0000
   4.500   0.7604   0.00875   0.00283  -0.0599   0.1296   1.0000
   4.750   0.7849   0.00901   0.00302  -0.0594   0.1146   1.0000
   5.000   0.8095   0.00927   0.00324  -0.0588   0.1009   1.0000
   5.250   0.8341   0.00955   0.00345  -0.0583   0.0878   1.0000
   5.500   0.8584   0.00985   0.00369  -0.0578   0.0733   1.0000
   5.750   0.8827   0.01016   0.00394  -0.0573   0.0618   1.0000
   6.000   0.9070   0.01047   0.00421  -0.0567   0.0519   1.0000
   6.250   0.9318   0.01073   0.00446  -0.0563   0.0466   1.0000
   6.500   0.9559   0.01106   0.00475  -0.0557   0.0389   1.0000
   6.750   0.9800   0.01137   0.00504  -0.0552   0.0332   1.0000
   7.000   1.0042   0.01169   0.00535  -0.0546   0.0286   1.0000
   7.250   1.0281   0.01202   0.00566  -0.0541   0.0247   1.0000
   7.500   1.0517   0.01237   0.00602  -0.0534   0.0203   1.0000
   7.750   1.0745   0.01279   0.00641  -0.0527   0.0154   1.0000
   8.000   1.0969   0.01326   0.00684  -0.0519   0.0101   1.0000
   8.250   1.1187   0.01377   0.00735  -0.0510   0.0064   1.0000
   8.500   1.1409   0.01423   0.00783  -0.0502   0.0054   1.0000
   8.750   1.1627   0.01472   0.00836  -0.0493   0.0045   1.0000
   9.000   1.1844   0.01520   0.00891  -0.0484   0.0042   1.0000
   9.250   1.2062   0.01567   0.00943  -0.0475   0.0040   1.0000
   9.500   1.2274   0.01617   0.00999  -0.0466   0.0038   1.0000
   9.750   1.2482   0.01668   0.01056  -0.0456   0.0035   1.0000
  10.000   1.2683   0.01723   0.01118  -0.0445   0.0033   1.0000
  10.250   1.2877   0.01783   0.01183  -0.0433   0.0031   1.0000
  10.500   1.3064   0.01845   0.01252  -0.0420   0.0030   1.0000
  10.750   1.3239   0.01915   0.01331  -0.0406   0.0028   1.0000
  11.000   1.3397   0.01990   0.01415  -0.0389   0.0027   1.0000
  11.250   1.3521   0.02079   0.01513  -0.0365   0.0026   1.0000
  11.500   1.3625   0.02173   0.01619  -0.0340   0.0025   1.0000
  11.750   1.3689   0.02295   0.01755  -0.0309   0.0024   1.0000
  12.000   1.3804   0.02377   0.01846  -0.0287   0.0024   1.0000
  12.250   1.3913   0.02464   0.01942  -0.0266   0.0023   1.0000
  12.500   1.4006   0.02562   0.02049  -0.0243   0.0023   1.0000
  12.750   1.4080   0.02675   0.02173  -0.0220   0.0023   1.0000
  13.000   1.4144   0.02797   0.02309  -0.0197   0.0022   1.0000
  13.250   1.4205   0.02924   0.02446  -0.0175   0.0022   1.0000
  13.500   1.4239   0.03075   0.02610  -0.0153   0.0022   1.0000
  13.750   1.4277   0.03228   0.02775  -0.0134   0.0022   1.0000
  14.000   1.4291   0.03408   0.02966  -0.0115   0.0021   1.0000
  14.250   1.4297   0.03604   0.03175  -0.0099   0.0021   1.0000
  14.500   1.4252   0.03858   0.03444  -0.0083   0.0021   1.0000
  14.750   1.4217   0.04120   0.03719  -0.0072   0.0021   1.0000
  15.000   1.4207   0.04372   0.03983  -0.0066   0.0020   1.0000
  15.250   1.4098   0.04755   0.04383  -0.0064   0.0020   1.0000
  15.500   1.3973   0.05196   0.04839  -0.0070   0.0020   1.0000
  15.750   1.3845   0.05685   0.05344  -0.0084   0.0020   1.0000
  16.000   1.3733   0.06204   0.05878  -0.0104   0.0020   1.0000
  16.250   1.3563   0.06871   0.06561  -0.0138   0.0020   1.0000
  16.500   1.3367   0.07659   0.07366  -0.0182   0.0020   1.0000
  16.750   1.3029   0.08804   0.08532  -0.0250   0.0020   1.0000
  17.000   1.2734   0.09920   0.09664  -0.0316   0.0020   1.0000
  17.250   1.2426   0.11085   0.10844  -0.0383   0.0020   1.0000
  17.500   1.2077   0.12366   0.12140  -0.0456   0.0021   1.0000
  17.750   1.1752   0.13615   0.13401  -0.0528   0.0021   1.0000
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