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USA 29 AIRFOIL (usa29-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 29 AIRFOIL (usa29-il)
Reynolds number: 200,000
Max Cl/Cd: 72.64 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa29-il-200000-n5.txt
Download as CSV file: xf-usa29-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 29 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2750   0.10157   0.09795  -0.0649   0.9850   0.0345
 -10.750  -0.2743   0.09549   0.09186  -0.0695   0.9805   0.0363
 -10.500  -0.2985   0.08364   0.08002  -0.0782   0.9749   0.0384
 -10.250  -0.2736   0.08297   0.07933  -0.0803   0.9720   0.0393
 -10.000  -0.2597   0.08101   0.07737  -0.0822   0.9661   0.0403
  -9.500  -0.4112   0.03818   0.03381  -0.1173   0.9318   0.0425
  -9.250  -0.4100   0.03494   0.03017  -0.1167   0.9226   0.0436
  -9.000  -0.3986   0.03227   0.02706  -0.1166   0.9161   0.0450
  -8.750  -0.3891   0.03038   0.02478  -0.1149   0.9080   0.0458
  -8.500  -0.3719   0.02888   0.02289  -0.1141   0.9016   0.0465
  -8.250  -0.3572   0.02680   0.02059  -0.1129   0.8952   0.0476
  -8.000  -0.3385   0.02561   0.01928  -0.1118   0.8880   0.0486
  -7.750  -0.3126   0.02442   0.01792  -0.1120   0.8835   0.0495
  -7.500  -0.2960   0.02350   0.01682  -0.1102   0.8748   0.0502
  -7.250  -0.2704   0.02242   0.01554  -0.1101   0.8694   0.0510
  -7.000  -0.2503   0.02160   0.01454  -0.1088   0.8611   0.0519
  -6.750  -0.2242   0.02071   0.01345  -0.1086   0.8547   0.0529
  -6.500  -0.2021   0.02002   0.01259  -0.1076   0.8464   0.0541
  -6.250  -0.1752   0.01930   0.01168  -0.1074   0.8393   0.0551
  -6.000  -0.1522   0.01869   0.01093  -0.1065   0.8303   0.0558
  -5.750  -0.1245   0.01806   0.01013  -0.1064   0.8228   0.0565
  -5.500  -0.1016   0.01757   0.00951  -0.1054   0.8128   0.0570
  -5.250  -0.0769   0.01683   0.00869  -0.1048   0.8040   0.0581
  -5.000  -0.0533   0.01630   0.00810  -0.1039   0.7938   0.0593
  -4.750  -0.0299   0.01588   0.00760  -0.1030   0.7831   0.0605
  -4.500  -0.0048   0.01550   0.00714  -0.1024   0.7727   0.0621
  -4.250   0.0195   0.01519   0.00673  -0.1016   0.7611   0.0640
  -4.000   0.0434   0.01490   0.00636  -0.1007   0.7486   0.0659
  -3.750   0.0679   0.01465   0.00599  -0.0999   0.7363   0.0675
  -3.500   0.0925   0.01440   0.00565  -0.0991   0.7237   0.0696
  -3.250   0.1175   0.01416   0.00536  -0.0985   0.7110   0.0729
  -3.000   0.1424   0.01398   0.00510  -0.0978   0.6985   0.0772
  -2.750   0.1671   0.01381   0.00489  -0.0971   0.6863   0.0857
  -2.500   0.1921   0.01366   0.00469  -0.0964   0.6752   0.0997
  -2.250   0.2173   0.01351   0.00447  -0.0959   0.6652   0.1166
  -2.000   0.2420   0.01335   0.00432  -0.0952   0.6555   0.1357
  -1.750   0.2669   0.01321   0.00424  -0.0947   0.6467   0.1653
  -1.500   0.2919   0.01316   0.00418  -0.0941   0.6382   0.1946
  -1.250   0.3168   0.01313   0.00414  -0.0935   0.6305   0.2146
  -1.000   0.3415   0.01313   0.00412  -0.0928   0.6230   0.2325
  -0.750   0.3661   0.01316   0.00417  -0.0922   0.6162   0.2541
  -0.500   0.3904   0.01322   0.00425  -0.0914   0.6090   0.2739
  -0.250   0.4154   0.01335   0.00432  -0.0908   0.6029   0.2915
   0.000   0.4397   0.01345   0.00443  -0.0900   0.5964   0.3069
   0.250   0.4642   0.01360   0.00451  -0.0893   0.5902   0.3204
   0.500   0.4887   0.01375   0.00462  -0.0886   0.5845   0.3325
   0.750   0.5123   0.01389   0.00473  -0.0877   0.5780   0.3436
   1.000   0.5369   0.01404   0.00480  -0.0870   0.5727   0.3530
   1.250   0.5609   0.01413   0.00489  -0.0862   0.5670   0.3600
   1.500   0.5848   0.01423   0.00494  -0.0854   0.5611   0.3666
   1.750   0.6095   0.01431   0.00499  -0.0848   0.5558   0.3716
   2.000   0.6333   0.01438   0.00507  -0.0840   0.5503   0.3769
   2.250   0.6573   0.01445   0.00513  -0.0832   0.5448   0.3815
   2.500   0.6816   0.01453   0.00519  -0.0826   0.5398   0.3870
   2.750   0.7047   0.01462   0.00529  -0.0817   0.5341   0.3932
   3.000   0.7282   0.01466   0.00538  -0.0809   0.5286   0.3986
   3.250   0.7523   0.01475   0.00545  -0.0802   0.5240   0.4039
   3.750   0.7980   0.01488   0.00567  -0.0783   0.5131   0.4117
   4.000   0.8213   0.01497   0.00577  -0.0775   0.5086   0.4162
   4.250   0.8436   0.01506   0.00592  -0.0765   0.5034   0.4216
   4.500   0.8651   0.01511   0.00605  -0.0753   0.4980   0.4271
   4.750   0.8874   0.01521   0.00618  -0.0743   0.4934   0.4331
   5.000   0.9092   0.01532   0.00635  -0.0732   0.4885   0.4379
   5.250   0.9303   0.01542   0.00653  -0.0720   0.4833   0.4424
   5.500   0.9524   0.01555   0.00670  -0.0709   0.4787   0.4468
   5.750   0.9742   0.01570   0.00690  -0.0699   0.4738   0.4518
   6.000   0.9953   0.01584   0.00714  -0.0687   0.4687   0.4587
   6.500   1.0401   0.01613   0.00761  -0.0670   0.4594   0.4858
   7.000   1.2000   0.01652   0.00911  -0.0910   0.4253   0.9957
   7.250   1.2251   0.01687   0.00946  -0.0909   0.4118   1.0000
   7.500   1.2319   0.01715   0.00972  -0.0869   0.4003   1.0000
   7.750   1.2362   0.01745   0.01002  -0.0824   0.3859   1.0000
   8.000   1.2427   0.01781   0.01039  -0.0785   0.3720   1.0000
   8.250   1.2472   0.01826   0.01081  -0.0744   0.3551   1.0000
   8.500   1.2494   0.01886   0.01134  -0.0700   0.3316   1.0000
   8.750   1.2460   0.01975   0.01207  -0.0650   0.2989   1.0000
   9.000   1.2359   0.02109   0.01316  -0.0594   0.2549   1.0000
   9.250   1.2206   0.02297   0.01471  -0.0536   0.2034   1.0000
   9.500   1.1917   0.02593   0.01719  -0.0470   0.1313   1.0000
   9.750   1.1634   0.02929   0.02015  -0.0413   0.0608   1.0000
  10.000   1.1524   0.03180   0.02254  -0.0378   0.0387   1.0000
  10.250   1.1512   0.03375   0.02452  -0.0354   0.0327   1.0000
  10.500   1.1533   0.03554   0.02639  -0.0335   0.0297   1.0000
  10.750   1.1560   0.03735   0.02831  -0.0317   0.0279   1.0000
  11.000   1.1560   0.03950   0.03056  -0.0301   0.0260   1.0000
  11.250   1.1544   0.04190   0.03305  -0.0285   0.0247   1.0000
  11.500   1.1558   0.04412   0.03538  -0.0273   0.0233   1.0000
  11.750   1.1563   0.04651   0.03789  -0.0262   0.0226   1.0000
  12.000   1.1574   0.04891   0.04039  -0.0253   0.0216   1.0000
  12.250   1.1559   0.05168   0.04327  -0.0244   0.0207   1.0000
  12.500   1.1540   0.05455   0.04623  -0.0237   0.0204   1.0000
  12.750   1.1502   0.05770   0.04948  -0.0231   0.0198   1.0000
  13.000   1.1467   0.06088   0.05276  -0.0226   0.0194   1.0000
  13.250   1.1382   0.06472   0.05668  -0.0222   0.0187   1.0000
  13.500   1.1363   0.06781   0.05986  -0.0218   0.0182   1.0000
  13.750   1.1336   0.07103   0.06317  -0.0215   0.0181   1.0000
  14.000   1.1352   0.07379   0.06602  -0.0213   0.0172   1.0000
  14.250   1.1340   0.07686   0.06916  -0.0210   0.0169   1.0000
  14.500   1.1351   0.07967   0.07205  -0.0209   0.0162   1.0000
  14.750   1.1360   0.08249   0.07492  -0.0207   0.0159   1.0000
  15.000   1.1380   0.08517   0.07766  -0.0204   0.0155   1.0000
  15.250   1.1405   0.08777   0.08030  -0.0202   0.0151   1.0000
  15.500   1.1436   0.09024   0.08281  -0.0199   0.0148   1.0000
  15.750   1.1476   0.09252   0.08513  -0.0195   0.0144   1.0000
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