Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SD2030-086-88 (sd2030-il)
Reynolds number: 50,000
Max Cl/Cd: 37.06 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd2030-il-50000-n5.txt
Download as CSV file: xf-sd2030-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4640   0.09110   0.08415  -0.0395   1.0000   0.0581
  -8.250  -0.4682   0.08779   0.08091  -0.0394   1.0000   0.0577
  -8.000  -0.4721   0.08440   0.07760  -0.0394   1.0000   0.0572
  -7.750  -0.4757   0.08091   0.07416  -0.0394   1.0000   0.0566
  -7.500  -0.4801   0.07734   0.07062  -0.0395   1.0000   0.0558
  -7.250  -0.4844   0.07371   0.06701  -0.0395   1.0000   0.0550
  -7.000  -0.4879   0.06998   0.06326  -0.0395   1.0000   0.0540
  -6.750  -0.4904   0.06609   0.05930  -0.0394   1.0000   0.0529
  -6.500  -0.4910   0.06205   0.05514  -0.0392   1.0000   0.0518
  -6.250  -0.4892   0.05792   0.05082  -0.0390   1.0000   0.0507
  -6.000  -0.4847   0.05370   0.04630  -0.0387   1.0000   0.0497
  -5.750  -0.4768   0.04964   0.04189  -0.0382   1.0000   0.0489
  -5.500  -0.4657   0.04584   0.03764  -0.0376   1.0000   0.0483
  -5.250  -0.4517   0.04240   0.03375  -0.0368   1.0000   0.0481
  -5.000  -0.4353   0.03938   0.03027  -0.0359   1.0000   0.0481
  -4.750  -0.4170   0.03671   0.02717  -0.0351   1.0000   0.0485
  -4.500  -0.3973   0.03438   0.02444  -0.0342   1.0000   0.0492
  -4.250  -0.3768   0.03258   0.02228  -0.0333   1.0000   0.0518
  -4.000  -0.3549   0.03088   0.02016  -0.0324   1.0000   0.0554
  -3.750  -0.3318   0.02926   0.01808  -0.0314   1.0000   0.0580
  -3.500  -0.3090   0.02764   0.01626  -0.0304   1.0000   0.0599
  -3.250  -0.2865   0.02640   0.01492  -0.0294   1.0000   0.0630
  -3.000  -0.2637   0.02536   0.01371  -0.0283   1.0000   0.0673
  -2.750  -0.2406   0.02440   0.01257  -0.0272   1.0000   0.0742
  -2.500  -0.2184   0.02363   0.01172  -0.0264   1.0000   0.0886
  -2.250  -0.1957   0.02276   0.01089  -0.0258   1.0000   0.1158
  -2.000  -0.1728   0.02155   0.01022  -0.0255   1.0000   0.1976
  -1.750  -0.1558   0.01940   0.00993  -0.0241   1.0000   0.5316
  -1.500  -0.1206   0.01852   0.00988  -0.0229   1.0000   1.0000
  -1.250  -0.1015   0.01864   0.00962  -0.0219   1.0000   1.0000
  -1.000  -0.0820   0.01880   0.00945  -0.0210   1.0000   1.0000
  -0.750  -0.0463   0.01919   0.00949  -0.0232   0.9938   1.0000
  -0.500  -0.0109   0.01956   0.00954  -0.0254   0.9865   1.0000
  -0.250   0.0246   0.01997   0.00969  -0.0276   0.9794   1.0000
   0.000   0.0607   0.02038   0.00990  -0.0298   0.9719   1.0000
   0.250   0.0944   0.02073   0.01006  -0.0316   0.9634   1.0000
   0.500   0.1326   0.02117   0.01035  -0.0341   0.9561   1.0000
   0.750   0.1648   0.02147   0.01055  -0.0355   0.9462   1.0000
   1.000   0.1988   0.02179   0.01078  -0.0372   0.9365   1.0000
   1.250   0.2368   0.02213   0.01106  -0.0395   0.9273   1.0000
   1.500   0.2714   0.02239   0.01129  -0.0412   0.9164   1.0000
   1.750   0.3045   0.02261   0.01151  -0.0424   0.9045   1.0000
   2.000   0.3386   0.02279   0.01171  -0.0438   0.8923   1.0000
   2.250   0.3735   0.02293   0.01189  -0.0451   0.8795   1.0000
   2.500   0.4090   0.02300   0.01202  -0.0465   0.8660   1.0000
   2.750   0.4447   0.02300   0.01213  -0.0477   0.8518   1.0000
   3.000   0.4811   0.02291   0.01214  -0.0488   0.8368   1.0000
   3.250   0.5184   0.02271   0.01208  -0.0498   0.8210   1.0000
   3.500   0.5559   0.02241   0.01196  -0.0507   0.8043   1.0000
   3.750   0.5851   0.02221   0.01191  -0.0501   0.7833   1.0000
   4.000   0.6196   0.02183   0.01169  -0.0501   0.7620   1.0000
   4.250   0.6477   0.02157   0.01163  -0.0490   0.7354   1.0000
   4.500   0.6778   0.02124   0.01145  -0.0482   0.7052   1.0000
   4.750   0.7048   0.02105   0.01136  -0.0468   0.6672   1.0000
   5.000   0.7352   0.02081   0.01115  -0.0458   0.6207   1.0000
   5.250   0.7627   0.02083   0.01112  -0.0444   0.5620   1.0000
   5.500   0.7860   0.02121   0.01125  -0.0427   0.4961   1.0000
   5.750   0.8044   0.02193   0.01166  -0.0405   0.4318   1.0000
   6.000   0.8206   0.02285   0.01230  -0.0384   0.3740   1.0000
   6.250   0.8359   0.02388   0.01307  -0.0364   0.3234   1.0000
   6.500   0.8517   0.02497   0.01398  -0.0346   0.2792   1.0000
   6.750   0.8679   0.02612   0.01504  -0.0330   0.2407   1.0000
   7.000   0.8850   0.02732   0.01612  -0.0316   0.2084   1.0000
   7.250   0.9031   0.02859   0.01731  -0.0304   0.1819   1.0000
   7.500   0.9227   0.02988   0.01863  -0.0293   0.1589   1.0000
   7.750   0.9420   0.03123   0.01994  -0.0283   0.1403   1.0000
   8.000   0.9644   0.03272   0.02152  -0.0276   0.1261   1.0000
   8.250   0.9847   0.03421   0.02315  -0.0267   0.1128   1.0000
   8.500   1.0055   0.03583   0.02487  -0.0259   0.1021   1.0000
   8.750   1.0286   0.03779   0.02715  -0.0252   0.0927   1.0000
   9.000   1.0464   0.03969   0.02923  -0.0241   0.0838   1.0000
   9.250   1.0648   0.04179   0.03148  -0.0231   0.0769   1.0000
   9.500   1.0780   0.04425   0.03436  -0.0215   0.0694   1.0000
   9.750   1.0909   0.04638   0.03653  -0.0201   0.0635   1.0000
  10.000   1.0970   0.04952   0.04022  -0.0179   0.0584   1.0000
  10.250   1.1010   0.05169   0.04267  -0.0158   0.0533   1.0000
  10.500   1.1047   0.05457   0.04568  -0.0140   0.0501   1.0000
  10.750   1.0952   0.05813   0.04976  -0.0108   0.0482   1.0000
  11.000   1.0832   0.06167   0.05369  -0.0082   0.0466   1.0000
  11.250   1.0695   0.06524   0.05755  -0.0062   0.0450   1.0000
  11.500   1.0547   0.06909   0.06163  -0.0051   0.0439   1.0000
  11.750   1.0365   0.07361   0.06638  -0.0049   0.0434   1.0000
  12.000   1.0099   0.07990   0.07293  -0.0065   0.0443   1.0000
  12.250   0.9791   0.08790   0.08114  -0.0103   0.0461   1.0000
  12.500   0.9528   0.09647   0.08976  -0.0155   0.0476   1.0000
<< Back to SD2030-086-88 (sd2030-il)

Polar data table (+)

Polar graphs


<< Back to SD2030-086-88 (sd2030-il)