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

SD7043 (9.1%) (sd7043-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SD7043 (9.1%) (sd7043-il)
Reynolds number: 500,000
Max Cl/Cd: 110.14 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7043-il-500000.txt
Download as CSV file: xf-sd7043-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7043 (9.1%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3517   0.08534   0.08317  -0.0400   1.0000   0.0195
  -8.250  -0.3652   0.08346   0.08136  -0.0375   1.0000   0.0195
  -8.000  -0.3740   0.07966   0.07760  -0.0376   0.9982   0.0198
  -7.750  -0.3560   0.07619   0.07412  -0.0418   0.9944   0.0202
  -7.500  -0.3380   0.07238   0.07032  -0.0470   0.9890   0.0206
  -7.250  -0.3130   0.06700   0.06492  -0.0562   0.9850   0.0210
  -7.000  -0.2872   0.06080   0.05870  -0.0674   0.9797   0.0218
  -6.750  -0.2544   0.05163   0.04942  -0.0833   0.9745   0.0228
  -6.500  -0.2229   0.03887   0.03591  -0.0989   0.9648   0.0248
  -6.250  -0.2060   0.03229   0.02914  -0.1030   0.9586   0.0259
  -6.000  -0.1908   0.02311   0.01903  -0.1042   0.9487   0.0186
  -5.750  -0.1674   0.01965   0.01506  -0.1045   0.9433   0.0183
  -5.500  -0.1438   0.01757   0.01260  -0.1039   0.9366   0.0185
  -5.250  -0.1173   0.01697   0.01170  -0.1034   0.9311   0.0194
  -5.000  -0.0933   0.01464   0.00912  -0.1030   0.9260   0.0204
  -4.750  -0.0678   0.01369   0.00808  -0.1025   0.9198   0.0212
  -4.500  -0.0417   0.01296   0.00726  -0.1020   0.9147   0.0223
  -4.250  -0.0154   0.01230   0.00650  -0.1015   0.9090   0.0236
  -4.000   0.0115   0.01197   0.00606  -0.1010   0.9029   0.0248
  -3.750   0.0371   0.01093   0.00500  -0.1006   0.8979   0.0274
  -3.500   0.0641   0.01050   0.00453  -0.1003   0.8913   0.0294
  -3.250   0.0912   0.01013   0.00409  -0.0999   0.8855   0.0312
  -3.000   0.1183   0.00960   0.00353  -0.0997   0.8796   0.0348
  -2.750   0.1458   0.00931   0.00320  -0.0994   0.8728   0.0383
  -2.500   0.1734   0.00898   0.00283  -0.0991   0.8672   0.0445
  -2.250   0.2011   0.00857   0.00253  -0.0990   0.8596   0.0746
  -2.000   0.2284   0.00804   0.00232  -0.0989   0.8532   0.1737
  -1.750   0.2558   0.00765   0.00222  -0.0990   0.8454   0.2649
  -1.500   0.2831   0.00732   0.00212  -0.0989   0.8383   0.3581
  -1.250   0.3105   0.00701   0.00208  -0.0988   0.8298   0.4532
  -1.000   0.3375   0.00673   0.00203  -0.0985   0.8221   0.5483
  -0.750   0.3640   0.00646   0.00204  -0.0980   0.8123   0.6433
  -0.500   0.3900   0.00626   0.00203  -0.0973   0.8033   0.7224
  -0.250   0.4153   0.00611   0.00202  -0.0964   0.7935   0.7877
   0.000   0.4387   0.00595   0.00201  -0.0950   0.7826   0.8556
   0.250   0.4610   0.00577   0.00193  -0.0932   0.7717   0.9282
   0.500   0.4958   0.00572   0.00182  -0.0944   0.7596   1.0000
   0.750   0.5238   0.00578   0.00179  -0.0943   0.7465   1.0000
   1.000   0.5517   0.00585   0.00177  -0.0942   0.7322   1.0000
   1.250   0.5795   0.00593   0.00176  -0.0940   0.7169   1.0000
   1.500   0.6071   0.00602   0.00177  -0.0938   0.7005   1.0000
   1.750   0.6346   0.00613   0.00180  -0.0936   0.6825   1.0000
   2.000   0.6619   0.00626   0.00183  -0.0934   0.6632   1.0000
   2.250   0.6889   0.00642   0.00188  -0.0931   0.6429   1.0000
   2.500   0.7159   0.00658   0.00195  -0.0928   0.6203   1.0000
   2.750   0.7424   0.00678   0.00203  -0.0925   0.5967   1.0000
   3.000   0.7689   0.00699   0.00213  -0.0922   0.5713   1.0000
   3.250   0.7952   0.00722   0.00226  -0.0918   0.5449   1.0000
   3.500   0.8212   0.00748   0.00240  -0.0915   0.5171   1.0000
   3.750   0.8469   0.00777   0.00255  -0.0911   0.4875   1.0000
   4.000   0.8723   0.00808   0.00273  -0.0906   0.4565   1.0000
   4.250   0.8977   0.00841   0.00293  -0.0902   0.4256   1.0000
   4.500   0.9227   0.00877   0.00315  -0.0898   0.3939   1.0000
   4.750   0.9476   0.00916   0.00339  -0.0893   0.3622   1.0000
   5.000   0.9723   0.00955   0.00366  -0.0889   0.3320   1.0000
   5.250   0.9968   0.00997   0.00393  -0.0884   0.3024   1.0000
   5.500   1.0213   0.01038   0.00422  -0.0879   0.2751   1.0000
   5.750   1.0457   0.01081   0.00453  -0.0874   0.2497   1.0000
   6.000   1.0698   0.01125   0.00486  -0.0869   0.2263   1.0000
   6.250   1.0941   0.01167   0.00520  -0.0864   0.2054   1.0000
   6.500   1.1182   0.01209   0.00554  -0.0859   0.1870   1.0000
   6.750   1.1420   0.01254   0.00592  -0.0853   0.1701   1.0000
   7.000   1.1655   0.01301   0.00631  -0.0848   0.1541   1.0000
   7.250   1.1890   0.01346   0.00672  -0.0842   0.1400   1.0000
   7.500   1.2124   0.01391   0.00713  -0.0835   0.1276   1.0000
   7.750   1.2355   0.01438   0.00757  -0.0829   0.1160   1.0000
   8.000   1.2582   0.01486   0.00803  -0.0822   0.1053   1.0000
   8.250   1.2804   0.01538   0.00853  -0.0814   0.0960   1.0000
   8.500   1.3012   0.01601   0.00911  -0.0804   0.0866   1.0000
   8.750   1.3237   0.01645   0.00960  -0.0797   0.0796   1.0000
   9.000   1.3439   0.01710   0.01023  -0.0787   0.0728   1.0000
   9.250   1.3648   0.01764   0.01080  -0.0777   0.0673   1.0000
   9.500   1.3829   0.01840   0.01156  -0.0764   0.0618   1.0000
   9.750   1.4035   0.01891   0.01214  -0.0754   0.0579   1.0000
  10.000   1.4204   0.01969   0.01291  -0.0739   0.0539   1.0000
  10.250   1.4364   0.02048   0.01377  -0.0723   0.0508   1.0000
  10.500   1.4541   0.02104   0.01441  -0.0709   0.0482   1.0000
  10.750   1.4681   0.02174   0.01514  -0.0689   0.0457   1.0000
  11.000   1.4750   0.02288   0.01633  -0.0660   0.0430   1.0000
  11.250   1.4867   0.02374   0.01728  -0.0639   0.0414   1.0000
  11.500   1.5005   0.02446   0.01809  -0.0622   0.0396   1.0000
  11.750   1.5127   0.02531   0.01901  -0.0604   0.0379   1.0000
  12.000   1.5219   0.02639   0.02015  -0.0584   0.0362   1.0000
  12.250   1.5233   0.02812   0.02194  -0.0557   0.0344   1.0000
  12.500   1.5311   0.02943   0.02337  -0.0539   0.0332   1.0000
  12.750   1.5430   0.03043   0.02449  -0.0525   0.0319   1.0000
  13.000   1.5538   0.03154   0.02568  -0.0512   0.0304   1.0000
  13.250   1.5623   0.03287   0.02706  -0.0499   0.0290   1.0000
  13.500   1.5635   0.03491   0.02916  -0.0483   0.0276   1.0000
  13.750   1.5631   0.03722   0.03158  -0.0468   0.0264   1.0000
  14.000   1.5728   0.03864   0.03313  -0.0460   0.0255   1.0000
  14.250   1.5790   0.04044   0.03504  -0.0452   0.0244   1.0000
  14.500   1.5844   0.04240   0.03709  -0.0445   0.0234   1.0000
  14.750   1.5868   0.04475   0.03953  -0.0440   0.0225   1.0000
  15.000   1.5824   0.04799   0.04287  -0.0437   0.0217   1.0000
  15.250   1.5701   0.05235   0.04734  -0.0436   0.0209   1.0000
  15.500   1.5747   0.05484   0.04999  -0.0439   0.0203   1.0000
  15.750   1.5757   0.05791   0.05320  -0.0443   0.0195   1.0000
  16.000   1.5749   0.06134   0.05675  -0.0451   0.0187   1.0000
  16.250   1.5727   0.06513   0.06066  -0.0462   0.0180   1.0000
  16.500   1.5670   0.06961   0.06524  -0.0477   0.0175   1.0000
  16.750   1.5565   0.07503   0.07078  -0.0498   0.0170   1.0000
  17.000   1.5419   0.08136   0.07723  -0.0524   0.0166   1.0000
<< Back to SD7043 (9.1%) (sd7043-il)

Polar data table (+)

Polar graphs


<< Back to SD7043 (9.1%) (sd7043-il)