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Ornithopter airfoil. (s1020-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Ornithopter airfoil. (s1020-il)
Reynolds number: 100,000
Max Cl/Cd: 53.41 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1020-il-100000-n5.txt
Download as CSV file: xf-s1020-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Ornithopter airfoil.                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2523   0.10671   0.10173  -0.0777   0.9718   0.0298
 -10.250  -0.2472   0.10213   0.09715  -0.0807   0.9664   0.0297
 -10.000  -0.2461   0.09525   0.09029  -0.0863   0.9625   0.0298
  -9.750  -0.2469   0.09020   0.08526  -0.0891   0.9553   0.0297
  -9.500  -0.2425   0.08467   0.07973  -0.0935   0.9509   0.0295
  -9.250  -0.2500   0.07802   0.07310  -0.0976   0.9428   0.0294
  -9.000  -0.2572   0.06970   0.06474  -0.1056   0.9370   0.0289
  -8.750  -0.2791   0.06295   0.05791  -0.1113   0.9254   0.0286
  -8.500  -0.2988   0.05796   0.05278  -0.1153   0.9133   0.0281
  -8.250  -0.3093   0.05281   0.04733  -0.1187   0.9034   0.0280
  -8.000  -0.3085   0.04808   0.04218  -0.1214   0.8962   0.0281
  -7.750  -0.3058   0.04458   0.03829  -0.1217   0.8880   0.0281
  -7.500  -0.2918   0.04099   0.03424  -0.1230   0.8825   0.0280
  -7.250  -0.2676   0.03760   0.03032  -0.1252   0.8797   0.0282
  -7.000  -0.2568   0.03564   0.02801  -0.1237   0.8714   0.0283
  -6.750  -0.2305   0.03328   0.02525  -0.1247   0.8677   0.0287
  -6.500  -0.1992   0.03119   0.02277  -0.1261   0.8653   0.0292
  -6.250  -0.1796   0.02992   0.02125  -0.1252   0.8590   0.0297
  -6.000  -0.1544   0.02855   0.01976  -0.1252   0.8543   0.0303
  -5.750  -0.1226   0.02736   0.01852  -0.1266   0.8515   0.0321
  -5.500  -0.0874   0.02624   0.01726  -0.1284   0.8494   0.0346
  -5.250  -0.0724   0.02571   0.01661  -0.1263   0.8413   0.0362
  -5.000  -0.0422   0.02465   0.01549  -0.1272   0.8377   0.0382
  -4.750  -0.0069   0.02368   0.01444  -0.1290   0.8352   0.0411
  -4.500   0.0173   0.02310   0.01372  -0.1287   0.8296   0.0449
  -4.250   0.0432   0.02241   0.01301  -0.1288   0.8240   0.0525
  -4.000   0.0787   0.02138   0.01206  -0.1307   0.8211   0.0807
  -3.750   0.1171   0.02024   0.01126  -0.1336   0.8189   0.1600
  -3.500   0.1325   0.01964   0.01123  -0.1323   0.8108   0.2752
  -3.250   0.1646   0.01916   0.01118  -0.1334   0.8069   0.3985
  -3.000   0.2021   0.01895   0.01092  -0.1352   0.8042   0.4534
  -2.750   0.2218   0.01907   0.01102  -0.1336   0.7971   0.4843
  -2.500   0.2516   0.01901   0.01090  -0.1339   0.7922   0.5126
  -2.250   0.2876   0.01885   0.01065  -0.1352   0.7891   0.5388
  -2.000   0.3090   0.01896   0.01072  -0.1340   0.7824   0.5584
  -1.750   0.3372   0.01892   0.01061  -0.1339   0.7771   0.5779
  -1.500   0.3728   0.01876   0.01035  -0.1353   0.7737   0.5973
  -1.250   0.3933   0.01888   0.01045  -0.1339   0.7668   0.6125
  -1.000   0.4215   0.01884   0.01035  -0.1339   0.7614   0.6279
  -0.750   0.4571   0.01867   0.01011  -0.1352   0.7580   0.6436
  -0.500   0.4751   0.01884   0.01027  -0.1334   0.7505   0.6571
  -0.250   0.5045   0.01878   0.01017  -0.1336   0.7454   0.6721
   0.000   0.5405   0.01860   0.00993  -0.1350   0.7420   0.6877
   0.250   0.5550   0.01884   0.01020  -0.1326   0.7336   0.7020
   0.500   0.5862   0.01875   0.01007  -0.1331   0.7290   0.7182
   0.750   0.6140   0.01874   0.01005  -0.1331   0.7238   0.7347
   1.000   0.6333   0.01887   0.01021  -0.1315   0.7166   0.7518
   1.250   0.6660   0.01873   0.01005  -0.1322   0.7123   0.7707
   1.500   0.6829   0.01892   0.01028  -0.1302   0.7050   0.7912
   1.750   0.7075   0.01887   0.01027  -0.1294   0.6993   0.8135
   2.000   0.7393   0.01869   0.01009  -0.1298   0.6953   0.8403
   2.250   0.7480   0.01891   0.01042  -0.1262   0.6868   0.8764
   2.500   0.7836   0.01870   0.01024  -0.1275   0.6821   0.9336
   2.750   0.8096   0.01889   0.01041  -0.1277   0.6749   1.0000
   3.000   0.8391   0.01903   0.01049  -0.1284   0.6688   1.0000
   3.250   0.8731   0.01908   0.01048  -0.1297   0.6637   1.0000
   3.500   0.8910   0.01945   0.01085  -0.1283   0.6558   1.0000
   3.750   0.9268   0.01945   0.01078  -0.1299   0.6508   1.0000
   4.000   0.9429   0.01985   0.01121  -0.1281   0.6427   1.0000
   4.250   0.9741   0.01994   0.01128  -0.1289   0.6369   1.0000
   4.500   0.9952   0.02024   0.01159  -0.1279   0.6297   1.0000
   4.750   1.0204   0.02045   0.01180  -0.1277   0.6229   1.0000
   5.000   1.0473   0.02063   0.01200  -0.1277   0.6165   1.0000
   5.250   1.0661   0.02096   0.01236  -0.1262   0.6087   1.0000
   5.500   1.0977   0.02105   0.01245  -0.1271   0.6027   1.0000
   5.750   1.1110   0.02151   0.01297  -0.1247   0.5942   1.0000
   6.000   1.1439   0.02156   0.01303  -0.1257   0.5880   1.0000
   6.250   1.1547   0.02207   0.01363  -0.1229   0.5790   1.0000
   6.500   1.1841   0.02218   0.01375  -0.1233   0.5720   1.0000
   6.750   1.1970   0.02267   0.01433  -0.1209   0.5630   1.0000
   7.000   1.2206   0.02291   0.01461  -0.1203   0.5552   1.0000
   7.250   1.2380   0.02330   0.01507  -0.1187   0.5463   1.0000
   7.500   1.2553   0.02371   0.01554  -0.1171   0.5375   1.0000
   7.750   1.2786   0.02394   0.01584  -0.1165   0.5289   1.0000
   8.000   1.2893   0.02454   0.01654  -0.1139   0.5190   1.0000
   8.250   1.3110   0.02483   0.01687  -0.1130   0.5100   1.0000
   8.500   1.3241   0.02536   0.01749  -0.1108   0.4997   1.0000
   8.750   1.3357   0.02598   0.01820  -0.1085   0.4891   1.0000
   9.000   1.3520   0.02643   0.01872  -0.1069   0.4784   1.0000
   9.250   1.3664   0.02695   0.01930  -0.1050   0.4672   1.0000
   9.500   1.3732   0.02779   0.02025  -0.1022   0.4551   1.0000
   9.750   1.3822   0.02858   0.02113  -0.0998   0.4427   1.0000
  10.000   1.3913   0.02940   0.02202  -0.0974   0.4298   1.0000
  10.250   1.3990   0.03030   0.02300  -0.0950   0.4161   1.0000
  10.500   1.4051   0.03133   0.02409  -0.0925   0.4016   1.0000
  10.750   1.4096   0.03252   0.02534  -0.0899   0.3864   1.0000
  11.000   1.4126   0.03385   0.02672  -0.0874   0.3704   1.0000
  11.250   1.4148   0.03532   0.02823  -0.0849   0.3537   1.0000
  11.500   1.4160   0.03693   0.02987  -0.0825   0.3362   1.0000
  11.750   1.4165   0.03869   0.03163  -0.0802   0.3184   1.0000
  12.000   1.4150   0.04068   0.03362  -0.0780   0.2994   1.0000
  12.250   1.4120   0.04294   0.03588  -0.0759   0.2796   1.0000
  12.500   1.4077   0.04542   0.03831  -0.0739   0.2597   1.0000
  12.750   1.4016   0.04820   0.04104  -0.0721   0.2390   1.0000
  13.000   1.3943   0.05127   0.04405  -0.0705   0.2175   1.0000
  13.250   1.3856   0.05463   0.04733  -0.0691   0.1971   1.0000
  13.500   1.3780   0.05809   0.05075  -0.0681   0.1766   1.0000
  14.000   1.3596   0.06585   0.05835  -0.0667   0.1369   1.0000
  14.250   1.3513   0.06985   0.06231  -0.0664   0.1197   1.0000
  14.500   1.3442   0.07386   0.06630  -0.0664   0.1050   1.0000
  14.750   1.3379   0.07789   0.07036  -0.0664   0.0921   1.0000
  15.000   1.3317   0.08200   0.07449  -0.0667   0.0803   1.0000
  15.250   1.3258   0.08619   0.07871  -0.0671   0.0699   1.0000
  15.500   1.3195   0.09054   0.08311  -0.0676   0.0607   1.0000
  15.750   1.3125   0.09508   0.08769  -0.0684   0.0527   1.0000
  16.000   1.3039   0.09995   0.09258  -0.0694   0.0461   1.0000
  16.250   1.2975   0.10459   0.09732  -0.0705   0.0405   1.0000
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