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=500,000 Ncrit=9


Details Polar file
Airfoil: SD2030-086-88 (sd2030-il)
Reynolds number: 500,000
Max Cl/Cd: 104.79 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd2030-il-500000.txt
Download as CSV file: xf-sd2030-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4600   0.08390   0.08170  -0.0379   1.0000   0.0199
  -8.750  -0.4681   0.08110   0.07892  -0.0369   1.0000   0.0203
  -8.500  -0.4792   0.07824   0.07611  -0.0363   1.0000   0.0204
  -8.250  -0.5042   0.07512   0.07307  -0.0353   1.0000   0.0203
  -8.000  -0.5223   0.07185   0.06982  -0.0353   1.0000   0.0203
  -7.750  -0.5298   0.06815   0.06611  -0.0360   0.9996   0.0204
  -7.500  -0.5112   0.06426   0.06216  -0.0408   0.9968   0.0211
  -7.250  -0.4903   0.05893   0.05673  -0.0473   0.9938   0.0218
  -7.000  -0.4712   0.05356   0.05122  -0.0525   0.9894   0.0227
  -6.750  -0.4471   0.04732   0.04473  -0.0579   0.9859   0.0246
  -6.500  -0.4125   0.04247   0.03928  -0.0621   0.9835   0.0269
  -6.250  -0.4073   0.03456   0.03113  -0.0637   0.9770   0.0286
  -6.000  -0.3796   0.03276   0.02923  -0.0655   0.9746   0.0300
  -5.750  -0.3497   0.03030   0.02655  -0.0674   0.9727   0.0323
  -5.500  -0.3100   0.03124   0.02706  -0.0685   0.9714   0.0363
  -5.000  -0.2724   0.01607   0.01034  -0.0663   0.9624   0.0209
  -4.750  -0.2396   0.01478   0.00891  -0.0675   0.9608   0.0213
  -4.500  -0.2054   0.01376   0.00778  -0.0689   0.9595   0.0218
  -4.250  -0.1702   0.01296   0.00691  -0.0705   0.9585   0.0226
  -4.000  -0.1346   0.01232   0.00623  -0.0722   0.9575   0.0240
  -3.750  -0.1119   0.01173   0.00558  -0.0711   0.9514   0.0246
  -3.500  -0.0804   0.01116   0.00495  -0.0718   0.9485   0.0258
  -3.250  -0.0473   0.01070   0.00444  -0.0729   0.9464   0.0268
  -3.000  -0.0143   0.01009   0.00379  -0.0739   0.9444   0.0312
  -2.750   0.0138   0.00972   0.00344  -0.0739   0.9402   0.0419
  -2.500   0.0400   0.00912   0.00314  -0.0737   0.9350   0.1160
  -2.250   0.0694   0.00855   0.00291  -0.0742   0.9316   0.2085
  -2.000   0.0978   0.00787   0.00271  -0.0746   0.9284   0.3525
  -1.750   0.1185   0.00716   0.00258  -0.0734   0.9209   0.5257
  -1.500   0.1414   0.00637   0.00250  -0.0721   0.9162   0.7340
  -1.250   0.1619   0.00613   0.00254  -0.0699   0.9088   0.8309
  -1.000   0.1875   0.00601   0.00246  -0.0688   0.9030   0.8696
  -0.750   0.2118   0.00595   0.00240  -0.0676   0.8955   0.8916
  -0.500   0.2362   0.00589   0.00233  -0.0662   0.8886   0.9160
  -0.250   0.2592   0.00587   0.00231  -0.0646   0.8801   0.9369
   0.000   0.2871   0.00583   0.00222  -0.0641   0.8730   0.9527
   0.250   0.3188   0.00583   0.00220  -0.0645   0.8637   0.9659
   0.500   0.3577   0.00583   0.00214  -0.0666   0.8556   0.9748
   0.750   0.3990   0.00583   0.00210  -0.0693   0.8459   0.9814
   1.000   0.4416   0.00582   0.00206  -0.0724   0.8348   0.9863
   1.250   0.4823   0.00582   0.00201  -0.0751   0.8230   0.9913
   1.500   0.5211   0.00582   0.00198  -0.0775   0.8099   0.9960
   1.750   0.5588   0.00582   0.00193  -0.0796   0.7937   1.0000
   2.000   0.5798   0.00585   0.00190  -0.0782   0.7762   1.0000
   2.250   0.6001   0.00589   0.00189  -0.0766   0.7552   1.0000
   2.500   0.6200   0.00598   0.00190  -0.0749   0.7306   1.0000
   2.750   0.6392   0.00610   0.00192  -0.0731   0.6996   1.0000
   3.000   0.6570   0.00630   0.00196  -0.0709   0.6595   1.0000
   3.250   0.6743   0.00657   0.00204  -0.0688   0.6135   1.0000
   3.500   0.6906   0.00694   0.00217  -0.0664   0.5591   1.0000
   3.750   0.7074   0.00738   0.00237  -0.0642   0.4990   1.0000
   4.000   0.7259   0.00785   0.00258  -0.0625   0.4427   1.0000
   4.250   0.7452   0.00834   0.00282  -0.0610   0.3861   1.0000
   4.500   0.7658   0.00882   0.00307  -0.0597   0.3353   1.0000
   4.750   0.7869   0.00930   0.00335  -0.0586   0.2884   1.0000
   5.000   0.8089   0.00974   0.00363  -0.0577   0.2496   1.0000
   5.250   0.8311   0.01019   0.00392  -0.0568   0.2154   1.0000
   5.500   0.8536   0.01063   0.00423  -0.0560   0.1830   1.0000
   5.750   0.8760   0.01109   0.00457  -0.0552   0.1543   1.0000
   6.000   0.8985   0.01155   0.00493  -0.0543   0.1296   1.0000
   6.250   0.9208   0.01203   0.00531  -0.0535   0.1078   1.0000
   6.500   0.9430   0.01253   0.00573  -0.0526   0.0901   1.0000
   6.750   0.9653   0.01301   0.00617  -0.0518   0.0762   1.0000
   7.000   0.9873   0.01353   0.00665  -0.0509   0.0649   1.0000
   7.250   1.0092   0.01403   0.00711  -0.0500   0.0552   1.0000
   7.500   1.0325   0.01440   0.00752  -0.0493   0.0494   1.0000
   7.750   1.0529   0.01505   0.00815  -0.0482   0.0429   1.0000
   8.000   1.0765   0.01536   0.00853  -0.0476   0.0393   1.0000
   8.250   1.0966   0.01601   0.00918  -0.0465   0.0332   1.0000
   8.500   1.1198   0.01634   0.00955  -0.0459   0.0280   1.0000
   8.750   1.1398   0.01700   0.01019  -0.0447   0.0204   1.0000
   9.000   1.1574   0.01791   0.01112  -0.0431   0.0154   1.0000
   9.250   1.1748   0.01878   0.01203  -0.0416   0.0134   1.0000
   9.500   1.1889   0.01993   0.01330  -0.0395   0.0121   1.0000
   9.750   1.2054   0.02078   0.01428  -0.0378   0.0113   1.0000
  10.000   1.2204   0.02169   0.01527  -0.0359   0.0105   1.0000
  10.250   1.2329   0.02264   0.01631  -0.0337   0.0098   1.0000
  10.500   1.2424   0.02380   0.01757  -0.0310   0.0096   1.0000
  10.750   1.2473   0.02541   0.01931  -0.0278   0.0092   1.0000
  11.000   1.2485   0.02754   0.02162  -0.0244   0.0089   1.0000
  11.250   1.2537   0.02933   0.02359  -0.0217   0.0087   1.0000
  11.500   1.2637   0.03041   0.02481  -0.0196   0.0085   1.0000
  11.750   1.2703   0.03185   0.02642  -0.0174   0.0082   1.0000
  12.000   1.2754   0.03344   0.02818  -0.0152   0.0080   1.0000
  12.250   1.2761   0.03558   0.03052  -0.0128   0.0079   1.0000
  12.500   1.2751   0.03787   0.03300  -0.0107   0.0079   1.0000
  12.750   1.2728   0.04032   0.03565  -0.0087   0.0077   1.0000
  13.000   1.2659   0.04340   0.03895  -0.0070   0.0077   1.0000
  13.250   1.2594   0.04648   0.04222  -0.0058   0.0077   1.0000
  13.500   1.2498   0.05012   0.04607  -0.0052   0.0076   1.0000
  13.750   1.2365   0.05450   0.05066  -0.0052   0.0076   1.0000
  14.000   1.2215   0.05948   0.05586  -0.0062   0.0076   1.0000
  14.250   1.2081   0.06462   0.06118  -0.0080   0.0075   1.0000
  14.500   1.1875   0.07159   0.06837  -0.0113   0.0076   1.0000
  14.750   1.1702   0.07867   0.07564  -0.0153   0.0077   1.0000
  15.000   1.1513   0.08685   0.08399  -0.0204   0.0076   1.0000
  15.250   1.1261   0.09717   0.09451  -0.0270   0.0077   1.0000
  15.500   1.1038   0.10749   0.10498  -0.0336   0.0078   1.0000
  15.750   1.0717   0.12080   0.11846  -0.0418   0.0080   1.0000
  16.000   1.0391   0.13508   0.13285  -0.0503   0.0082   1.0000
<< Back to SD2030-086-88 (sd2030-il)

Polar data table (+)

Polar graphs


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