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

S1016 (s1016-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S1016 (s1016-il)
Reynolds number: 200,000
Max Cl/Cd: 35.28 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1016-il-200000.txt
Download as CSV file: xf-s1016-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1016                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.000  -0.9048   0.10863   0.10436  -0.0514   1.0000   0.0519
 -18.750  -0.9707   0.09356   0.08889  -0.0603   1.0000   0.0512
 -18.500  -0.9998   0.08555   0.08063  -0.0646   1.0000   0.0516
 -18.250  -1.0209   0.07925   0.07411  -0.0678   1.0000   0.0523
 -18.000  -1.0395   0.07359   0.06821  -0.0702   1.0000   0.0529
 -17.750  -1.0566   0.06850   0.06287  -0.0721   1.0000   0.0536
 -17.500  -1.0735   0.06393   0.05803  -0.0735   1.0000   0.0543
 -17.250  -1.0672   0.06133   0.05542  -0.0739   1.0000   0.0557
 -17.000  -1.0582   0.05952   0.05365  -0.0744   1.0000   0.0572
 -16.750  -1.0575   0.05694   0.05097  -0.0749   1.0000   0.0585
 -16.500  -1.0597   0.05419   0.04806  -0.0752   1.0000   0.0599
 -16.250  -1.0642   0.05145   0.04511  -0.0752   1.0000   0.0614
 -16.000  -1.0693   0.04890   0.04231  -0.0748   1.0000   0.0625
 -15.750  -1.0532   0.04740   0.04091  -0.0749   1.0000   0.0649
 -15.500  -1.0457   0.04593   0.03942  -0.0747   1.0000   0.0668
 -15.250  -1.0429   0.04430   0.03768  -0.0739   1.0000   0.0687
 -15.000  -1.0442   0.04274   0.03594  -0.0725   1.0000   0.0705
 -14.750  -1.0541   0.04168   0.03469  -0.0692   1.0000   0.0717
 -14.500  -1.0401   0.04059   0.03370  -0.0683   0.9982   0.0743
 -14.250  -1.0258   0.03935   0.03244  -0.0687   0.9925   0.0770
 -14.000  -1.0137   0.03797   0.03090  -0.0689   0.9892   0.0799
 -13.750  -0.9977   0.03654   0.02931  -0.0693   0.9868   0.0830
 -13.500  -0.9771   0.03546   0.02831  -0.0701   0.9849   0.0864
 -13.250  -0.9591   0.03435   0.02708  -0.0708   0.9831   0.0901
 -13.000  -0.9418   0.03317   0.02570  -0.0713   0.9814   0.0936
 -12.750  -0.9187   0.03220   0.02483  -0.0719   0.9798   0.0978
 -12.500  -0.9024   0.03137   0.02393  -0.0718   0.9774   0.1020
 -12.250  -0.8849   0.03047   0.02285  -0.0718   0.9752   0.1062
 -12.000  -0.8612   0.02959   0.02207  -0.0724   0.9735   0.1110
 -11.750  -0.8407   0.02881   0.02120  -0.0728   0.9717   0.1163
 -11.500  -0.8173   0.02797   0.02034  -0.0733   0.9704   0.1218
 -11.250  -0.7956   0.02726   0.01964  -0.0737   0.9692   0.1274
 -11.000  -0.7753   0.02665   0.01887  -0.0738   0.9678   0.1333
 -10.750  -0.7581   0.02605   0.01839  -0.0730   0.9660   0.1394
 -10.500  -0.7440   0.02563   0.01790  -0.0717   0.9640   0.1456
 -10.250  -0.7264   0.02508   0.01739  -0.0709   0.9624   0.1523
 -10.000  -0.7109   0.02469   0.01697  -0.0699   0.9607   0.1595
  -9.750  -0.6920   0.02418   0.01649  -0.0693   0.9591   0.1673
  -9.500  -0.6727   0.02374   0.01602  -0.0689   0.9574   0.1764
  -9.250  -0.6537   0.02325   0.01559  -0.0684   0.9562   0.1855
  -9.000  -0.6351   0.02294   0.01521  -0.0677   0.9551   0.1955
  -8.750  -0.6213   0.02257   0.01496  -0.0662   0.9538   0.2054
  -8.500  -0.6323   0.02281   0.01514  -0.0596   0.9508   0.2117
  -8.250  -0.6427   0.02283   0.01526  -0.0533   0.9476   0.2181
  -8.000  -0.6468   0.02285   0.01526  -0.0482   0.9455   0.2269
  -7.750  -0.6394   0.02257   0.01507  -0.0453   0.9435   0.2387
  -7.500  -0.6311   0.02232   0.01489  -0.0426   0.9419   0.2526
  -7.250  -0.6247   0.02213   0.01476  -0.0396   0.9407   0.2676
  -7.000  -0.6287   0.02207   0.01475  -0.0344   0.9384   0.2818
  -6.750  -0.6648   0.02225   0.01496  -0.0231   0.9353   0.2853
  -6.500  -0.6791   0.02218   0.01490  -0.0159   0.9324   0.2979
  -6.250  -0.6907   0.02203   0.01484  -0.0091   0.9300   0.3130
  -6.000  -0.6925   0.02180   0.01472  -0.0042   0.9274   0.3348
  -5.750  -0.6884   0.02151   0.01460  -0.0004   0.9256   0.3646
  -5.500  -0.6918   0.02123   0.01449   0.0049   0.9226   0.3945
  -5.250  -0.7068   0.02089   0.01428   0.0125   0.9196   0.4219
  -5.000  -0.7090   0.02042   0.01406   0.0176   0.9161   0.4636
  -4.750  -0.7037   0.01996   0.01393   0.0215   0.9133   0.5209
  -4.500  -0.6814   0.01978   0.01428   0.0227   0.9105   0.6019
  -4.250  -0.6222   0.02121   0.01615   0.0185   0.9088   0.6746
  -4.000  -0.6225   0.02179   0.01678   0.0244   0.9037   0.7001
  -3.750  -0.6144   0.02204   0.01697   0.0281   0.8988   0.7267
  -3.500  -0.5838   0.02280   0.01766   0.0279   0.8952   0.7442
  -3.250  -0.5411   0.02377   0.01852   0.0256   0.8925   0.7589
  -3.000  -0.5385   0.02440   0.01916   0.0310   0.8850   0.7656
  -2.750  -0.5116   0.02497   0.01966   0.0315   0.8803   0.7769
  -2.500  -0.4590   0.02620   0.02085   0.0280   0.8778   0.7816
  -2.250  -0.4561   0.02642   0.02103   0.0326   0.8699   0.7931
  -2.000  -0.4149   0.02740   0.02199   0.0311   0.8656   0.7969
  -1.750  -0.3630   0.02836   0.02292   0.0276   0.8626   0.8019
  -1.500  -0.3194   0.02884   0.02335   0.0250   0.8601   0.8104
  -1.250  -0.3016   0.02948   0.02399   0.0275   0.8510   0.8143
  -1.000  -0.2803   0.02948   0.02394   0.0288   0.8457   0.8260
  -0.750  -0.2075   0.03036   0.02481   0.0214   0.8445   0.8272
  -0.500  -0.1230   0.03115   0.02558   0.0117   0.8438   0.8283
  -0.250  -0.0677   0.03168   0.02613   0.0070   0.8373   0.8308
   0.000   0.0005   0.03184   0.02629  -0.0001   0.8334   0.8334
   0.250   0.0669   0.03168   0.02613  -0.0069   0.8308   0.8374
   0.500   0.1233   0.03115   0.02558  -0.0118   0.8283   0.8438
   0.750   0.2073   0.03036   0.02480  -0.0214   0.8272   0.8445
   1.000   0.2802   0.02950   0.02396  -0.0288   0.8260   0.8458
   1.500   0.3199   0.02881   0.02331  -0.0251   0.8103   0.8601
   1.750   0.3634   0.02835   0.02291  -0.0276   0.8019   0.8626
   2.000   0.4144   0.02741   0.02200  -0.0310   0.7969   0.8655
   2.250   0.4561   0.02641   0.02102  -0.0326   0.7931   0.8699
   2.500   0.4589   0.02619   0.02084  -0.0279   0.7816   0.8778
   2.750   0.5115   0.02498   0.01967  -0.0315   0.7769   0.8804
   3.000   0.5383   0.02441   0.01917  -0.0310   0.7657   0.8851
   3.250   0.5412   0.02380   0.01855  -0.0257   0.7590   0.8926
   3.500   0.5834   0.02282   0.01767  -0.0279   0.7443   0.8952
   3.750   0.6142   0.02204   0.01697  -0.0280   0.7268   0.8988
   4.000   0.6222   0.02180   0.01679  -0.0244   0.7004   0.9037
   4.250   0.6224   0.02121   0.01614  -0.0186   0.6747   0.9088
   4.500   0.6818   0.01977   0.01427  -0.0228   0.6021   0.9105
   4.750   0.7038   0.01995   0.01392  -0.0215   0.5215   0.9134
   5.000   0.7089   0.02041   0.01405  -0.0176   0.4642   0.9160
   5.250   0.7066   0.02089   0.01428  -0.0124   0.4218   0.9196
   5.500   0.6915   0.02122   0.01448  -0.0048   0.3947   0.9226
   5.750   0.6884   0.02151   0.01459   0.0004   0.3643   0.9256
   6.000   0.6924   0.02179   0.01471   0.0042   0.3348   0.9274
   6.250   0.6908   0.02202   0.01482   0.0091   0.3130   0.9300
   6.500   0.6788   0.02217   0.01489   0.0159   0.2978   0.9324
   6.750   0.6647   0.02224   0.01494   0.0231   0.2853   0.9353
   7.000   0.6278   0.02205   0.01473   0.0346   0.2821   0.9384
   7.250   0.6248   0.02212   0.01475   0.0396   0.2678   0.9407
   7.500   0.6312   0.02231   0.01488   0.0426   0.2527   0.9420
   7.750   0.6396   0.02255   0.01505   0.0453   0.2390   0.9435
   8.000   0.6466   0.02283   0.01524   0.0482   0.2269   0.9456
   8.250   0.6422   0.02280   0.01523   0.0534   0.2182   0.9476
   8.500   0.6322   0.02279   0.01512   0.0597   0.2120   0.9508
   8.750   0.6211   0.02254   0.01493   0.0662   0.2056   0.9539
   9.000   0.6354   0.02292   0.01519   0.0676   0.1953   0.9551
   9.250   0.6540   0.02323   0.01558   0.0683   0.1853   0.9562
   9.500   0.6732   0.02372   0.01601   0.0688   0.1762   0.9575
   9.750   0.6926   0.02417   0.01647   0.0692   0.1673   0.9592
  10.000   0.7113   0.02467   0.01695   0.0698   0.1593   0.9607
  10.250   0.7270   0.02507   0.01738   0.0709   0.1523   0.9624
  10.500   0.7442   0.02561   0.01788   0.0717   0.1455   0.9641
  10.750   0.7587   0.02603   0.01837   0.0729   0.1394   0.9661
  11.000   0.7768   0.02666   0.01886   0.0736   0.1330   0.9679
  11.250   0.7966   0.02726   0.01963   0.0736   0.1272   0.9692
  11.500   0.8182   0.02796   0.02033   0.0732   0.1216   0.9705
  11.750   0.8415   0.02881   0.02120   0.0727   0.1160   0.9718
  12.000   0.8623   0.02957   0.02206   0.0722   0.1110   0.9736
  12.250   0.8869   0.03048   0.02284   0.0716   0.1059   0.9752
  12.500   0.9034   0.03136   0.02392   0.0716   0.1019   0.9775
  12.750   0.9200   0.03219   0.02482   0.0717   0.0977   0.9799
  13.000   0.9445   0.03320   0.02570   0.0710   0.0934   0.9814
  13.250   0.9604   0.03434   0.02708   0.0705   0.0900   0.9832
  13.500   0.9786   0.03545   0.02828   0.0698   0.0863   0.9850
  13.750   0.9998   0.03653   0.02929   0.0690   0.0828   0.9869
  14.000   1.0153   0.03797   0.03090   0.0686   0.0798   0.9894
  14.250   1.0279   0.03934   0.03243   0.0684   0.0770   0.9927
  14.500   1.0420   0.04058   0.03368   0.0680   0.0742   0.9986
  14.750   1.0543   0.04160   0.03461   0.0693   0.0717   1.0000
  15.000   1.0454   0.04270   0.03590   0.0723   0.0705   1.0000
  15.250   1.0441   0.04426   0.03764   0.0737   0.0687   1.0000
  15.500   1.0474   0.04589   0.03938   0.0744   0.0667   1.0000
  15.750   1.0549   0.04732   0.04081   0.0747   0.0648   1.0000
  16.000   1.0717   0.04889   0.04229   0.0745   0.0625   1.0000
  16.250   1.0654   0.05145   0.04511   0.0749   0.0613   1.0000
  16.500   1.0618   0.05414   0.04802   0.0749   0.0599   1.0000
  16.750   1.0595   0.05690   0.05093   0.0747   0.0585   1.0000
  17.000   1.0608   0.05940   0.05352   0.0742   0.0571   1.0000
  17.250   1.0692   0.06133   0.05542   0.0737   0.0557   1.0000
  17.500   1.0752   0.06393   0.05803   0.0732   0.0542   1.0000
  17.750   1.0585   0.06847   0.06284   0.0718   0.0535   1.0000
  18.000   1.0413   0.07358   0.06820   0.0700   0.0528   1.0000
  18.250   1.0225   0.07927   0.07412   0.0675   0.0521   1.0000
  18.500   1.0014   0.08562   0.08071   0.0643   0.0517   1.0000
  18.750   0.9717   0.09374   0.08907   0.0599   0.0513   1.0000
  19.000   0.9114   0.10782   0.10353   0.0516   0.0518   1.0000
<< Back to S1016 (s1016-il)

Polar data table (+)

Polar graphs


<< Back to S1016 (s1016-il)