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USA 31 AIRFOIL (usa31-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 31 AIRFOIL (usa31-il)
Reynolds number: 100,000
Max Cl/Cd: 40.84 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa31-il-100000-n5.txt
Download as CSV file: xf-usa31-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 31 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250   0.1051   0.10280   0.09750  -0.1069   0.8635   0.0764
  -8.000   0.1190   0.10002   0.09471  -0.1088   0.8603   0.0784
  -7.250   0.0782   0.09738   0.09220  -0.1062   0.8329   0.0831
  -7.000   0.0882   0.09393   0.08875  -0.1068   0.8288   0.0838
  -6.750   0.1257   0.08986   0.08466  -0.1072   0.8280   0.0863
  -6.500   0.1207   0.08867   0.08350  -0.1043   0.8189   0.0880
  -6.250   0.1203   0.08679   0.08163  -0.1037   0.8123   0.0910
  -6.000   0.0956   0.08613   0.08098  -0.1060   0.7986   0.0944
  -5.750   0.1074   0.08253   0.07737  -0.1078   0.7942   0.0951
  -5.500   0.1285   0.07912   0.07393  -0.1074   0.7921   0.0961
  -5.000   0.1323   0.06844   0.06303  -0.1135   0.7751   0.0645
  -4.500   0.1480   0.06521   0.05981  -0.1091   0.7603   0.0607
  -4.000   0.1818   0.04716   0.04098  -0.1245   0.7465   0.0505
  -3.750   0.2070   0.04253   0.03598  -0.1277   0.7419   0.0501
  -3.500   0.2375   0.03851   0.03151  -0.1305   0.7391   0.0495
  -3.250   0.2521   0.03638   0.02900  -0.1296   0.7316   0.0491
  -3.000   0.2730   0.03442   0.02663  -0.1292   0.7255   0.0488
  -2.750   0.3037   0.03243   0.02421  -0.1298   0.7223   0.0486
  -2.500   0.3384   0.03064   0.02203  -0.1308   0.7199   0.0486
  -2.250   0.3457   0.03048   0.02168  -0.1275   0.7096   0.0487
  -2.000   0.3766   0.02929   0.02021  -0.1276   0.7057   0.0489
  -1.750   0.4131   0.02806   0.01870  -0.1286   0.7030   0.0496
  -1.500   0.4254   0.02806   0.01852  -0.1259   0.6940   0.0504
  -1.250   0.4543   0.02726   0.01768  -0.1258   0.6892   0.0513
  -1.000   0.4910   0.02631   0.01667  -0.1269   0.6859   0.0527
  -0.750   0.5069   0.02628   0.01660  -0.1247   0.6780   0.0532
  -0.500   0.5341   0.02587   0.01611  -0.1242   0.6722   0.0538
  -0.250   0.5710   0.02519   0.01533  -0.1253   0.6685   0.0548
   0.000   0.5900   0.02521   0.01529  -0.1236   0.6611   0.0557
   0.250   0.6160   0.02503   0.01501  -0.1230   0.6547   0.0568
   0.500   0.6546   0.02443   0.01432  -0.1246   0.6505   0.0587
   0.750   0.6750   0.02449   0.01434  -0.1233   0.6430   0.0617
   1.000   0.7026   0.02433   0.01410  -0.1231   0.6364   0.0657
   1.250   0.7441   0.02375   0.01344  -0.1253   0.6319   0.0739
   1.500   0.7717   0.02358   0.01364  -0.1258   0.6243   0.1539
   1.750   0.7879   0.02397   0.01430  -0.1233   0.6172   0.2425
   2.000   0.8247   0.02403   0.01415  -0.1243   0.6124   0.2783
   2.250   0.8312   0.02477   0.01487  -0.1206   0.6037   0.2917
   2.500   0.8572   0.02502   0.01498  -0.1201   0.5974   0.3074
   2.750   0.8876   0.02512   0.01499  -0.1203   0.5917   0.3202
   3.000   0.8952   0.02576   0.01565  -0.1169   0.5831   0.3300
   3.250   0.9226   0.02587   0.01568  -0.1167   0.5772   0.3470
   3.500   0.9427   0.02618   0.01590  -0.1154   0.5706   0.3579
   3.750   0.9581   0.02648   0.01621  -0.1135   0.5630   0.3618
   4.000   0.9904   0.02636   0.01597  -0.1143   0.5574   0.3659
   4.250   1.0040   0.02684   0.01642  -0.1122   0.5500   0.3683
   4.500   1.0245   0.02715   0.01666  -0.1112   0.5431   0.3712
   4.750   1.0616   0.02702   0.01642  -0.1129   0.5380   0.3747
   5.000   1.0712   0.02773   0.01717  -0.1104   0.5299   0.3768
   5.250   1.0972   0.02796   0.01734  -0.1105   0.5236   0.3791
   5.500   1.1300   0.02801   0.01729  -0.1116   0.5183   0.3816
   5.750   1.1389   0.02879   0.01812  -0.1090   0.5107   0.3833
   6.000   1.1642   0.02903   0.01829  -0.1089   0.5048   0.3860
   6.250   1.1908   0.02927   0.01852  -0.1091   0.4991   0.3888
   6.500   1.2029   0.03000   0.01931  -0.1073   0.4921   0.3913
   6.750   1.2289   0.03020   0.01947  -0.1073   0.4865   0.3942
   7.000   1.2501   0.03061   0.01988  -0.1067   0.4809   0.3968
   7.250   1.2601   0.03142   0.02074  -0.1045   0.4740   0.3988
   7.500   1.2847   0.03167   0.02097  -0.1043   0.4688   0.4010
   7.750   1.3047   0.03212   0.02144  -0.1036   0.4631   0.4034
   8.000   1.3128   0.03306   0.02246  -0.1013   0.4565   0.4055
   8.250   1.3356   0.03335   0.02272  -0.1009   0.4509   0.4090
   8.500   1.3530   0.03392   0.02330  -0.0998   0.4454   0.4126
   8.750   1.3582   0.03502   0.02451  -0.0973   0.4384   0.4150
   9.000   1.3804   0.03531   0.02479  -0.0968   0.4327   0.4190
   9.250   1.3924   0.03615   0.02568  -0.0952   0.4267   0.4224
   9.500   1.3974   0.03735   0.02696  -0.0929   0.4199   0.4248
   9.750   1.4188   0.03769   0.02729  -0.0923   0.4146   0.4285
  10.000   1.4290   0.03871   0.02838  -0.0907   0.4090   0.4316
  10.250   1.4313   0.04018   0.02997  -0.0883   0.4025   0.4347
  10.500   1.4499   0.04070   0.03050  -0.0876   0.3973   0.4396
  10.750   1.4622   0.04163   0.03150  -0.0863   0.3919   0.4450
  11.000   1.4587   0.04359   0.03362  -0.0836   0.3853   0.4499
  11.750   1.5175   0.04766   0.03867  -0.0868   0.3667   1.0000
  12.000   1.5321   0.04842   0.03942  -0.0857   0.3615   1.0000
  12.250   1.5341   0.05023   0.04130  -0.0838   0.3556   1.0000
  12.500   1.5260   0.05294   0.04414  -0.0814   0.3486   1.0000
  12.750   1.5430   0.05343   0.04459  -0.0806   0.3430   1.0000
  13.000   1.5282   0.05693   0.04826  -0.0781   0.3357   1.0000
  13.250   1.5272   0.05923   0.05064  -0.0766   0.3292   1.0000
  13.500   1.5422   0.05990   0.05128  -0.0757   0.3235   1.0000
  13.750   1.5177   0.06482   0.05640  -0.0736   0.3152   1.0000
  14.000   1.5315   0.06557   0.05711  -0.0727   0.3089   1.0000
  14.250   1.5094   0.07058   0.06229  -0.0712   0.3008   1.0000
  14.500   1.5114   0.07280   0.06456  -0.0703   0.2940   1.0000
  14.750   1.5071   0.07589   0.06771  -0.0694   0.2874   1.0000
  15.000   1.4931   0.08030   0.07224  -0.0687   0.2797   1.0000
  15.250   1.5156   0.07997   0.07185  -0.0680   0.2750   1.0000
  15.500   1.4798   0.08747   0.07958  -0.0676   0.2665   1.0000
  15.750   1.4880   0.08907   0.08120  -0.0671   0.2613   1.0000
  16.000   1.4832   0.09251   0.08471  -0.0668   0.2553   1.0000
  16.250   1.4666   0.09772   0.09005  -0.0668   0.2481   1.0000
  16.500   1.4867   0.09758   0.08990  -0.0662   0.2439   1.0000
  16.750   1.4557   0.10504   0.09753  -0.0669   0.2362   1.0000
  17.000   1.4589   0.10743   0.09996  -0.0668   0.2306   1.0000
  17.250   1.4750   0.10783   0.10035  -0.0663   0.2262   1.0000
  17.500   1.4396   0.11630   0.10901  -0.0678   0.2183   1.0000
  17.750   1.4566   0.11652   0.10923  -0.0674   0.2138   1.0000
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