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NLR-7301 AIRFOIL (nlr7301-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NLR-7301 AIRFOIL (nlr7301-il)
Reynolds number: 200,000
Max Cl/Cd: 30.96 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlr7301-il-200000.txt
Download as CSV file: xf-nlr7301-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLR-7301 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.7040   0.10229   0.09755  -0.0504   1.0000   0.0641
 -14.500  -0.7581   0.08820   0.08329  -0.0588   1.0000   0.0632
 -14.250  -0.8424   0.07303   0.06771  -0.0677   1.0000   0.0618
 -14.000  -0.8929   0.06453   0.05887  -0.0713   1.0000   0.0614
 -13.750  -0.9234   0.05896   0.05302  -0.0728   1.0000   0.0613
 -13.500  -0.9432   0.05477   0.04859  -0.0732   1.0000   0.0615
 -13.250  -0.9575   0.05131   0.04490  -0.0731   1.0000   0.0618
 -13.000  -0.9685   0.04832   0.04169  -0.0724   1.0000   0.0622
 -12.750  -0.9779   0.04576   0.03891  -0.0710   1.0000   0.0625
 -12.500  -0.9898   0.04381   0.03678  -0.0683   1.0000   0.0629
 -12.250  -1.0132   0.04289   0.03576  -0.0624   1.0000   0.0630
 -12.000  -1.0357   0.04204   0.03479  -0.0565   1.0000   0.0632
 -11.750  -1.0505   0.04090   0.03349  -0.0516   1.0000   0.0635
 -11.500  -1.0600   0.03966   0.03204  -0.0475   1.0000   0.0639
 -11.250  -1.0658   0.03840   0.03054  -0.0438   1.0000   0.0644
 -11.000  -1.0509   0.03712   0.02931  -0.0423   1.0000   0.0651
 -10.750  -1.0258   0.03607   0.02829  -0.0429   0.9982   0.0662
 -10.500  -0.9972   0.03500   0.02717  -0.0442   0.9955   0.0676
 -10.250  -0.9692   0.03370   0.02569  -0.0457   0.9930   0.0693
 -10.000  -0.9449   0.03240   0.02413  -0.0464   0.9898   0.0707
  -9.750  -0.9159   0.03137   0.02322  -0.0470   0.9876   0.0721
  -9.500  -0.8873   0.03052   0.02236  -0.0479   0.9849   0.0737
  -9.250  -0.8572   0.02964   0.02139  -0.0491   0.9824   0.0757
  -9.000  -0.8251   0.02869   0.02033  -0.0506   0.9804   0.0779
  -8.750  -0.7973   0.02799   0.01976  -0.0510   0.9776   0.0800
  -8.500  -0.7727   0.02735   0.01908  -0.0511   0.9736   0.0824
  -8.250  -0.7448   0.02665   0.01827  -0.0516   0.9707   0.0850
  -8.000  -0.7148   0.02594   0.01772  -0.0524   0.9686   0.0876
  -7.750  -0.6828   0.02537   0.01713  -0.0538   0.9667   0.0913
  -7.500  -0.6531   0.02472   0.01655  -0.0547   0.9648   0.0948
  -7.250  -0.6383   0.02429   0.01616  -0.0529   0.9595   0.0980
  -7.000  -0.6115   0.02373   0.01559  -0.0532   0.9560   0.1023
  -6.750  -0.5821   0.02316   0.01513  -0.0542   0.9534   0.1074
  -6.500  -0.5511   0.02257   0.01459  -0.0555   0.9515   0.1136
  -6.250  -0.5174   0.02212   0.01416  -0.0573   0.9499   0.1212
  -6.000  -0.5095   0.02166   0.01382  -0.0545   0.9442   0.1266
  -5.750  -0.4858   0.02115   0.01338  -0.0545   0.9403   0.1356
  -5.500  -0.4561   0.02058   0.01290  -0.0557   0.9373   0.1478
  -5.250  -0.4244   0.01990   0.01239  -0.0575   0.9353   0.1650
  -5.000  -0.3901   0.01913   0.01186  -0.0600   0.9336   0.1948
  -4.750  -0.3532   0.01779   0.01110  -0.0639   0.9324   0.2825
  -4.500  -0.3329   0.01649   0.01086  -0.0646   0.9280   0.4606
  -4.250  -0.3097   0.01674   0.01136  -0.0636   0.9237   0.5362
  -4.000  -0.2817   0.01715   0.01180  -0.0634   0.9206   0.5669
  -3.750  -0.2505   0.01761   0.01228  -0.0635   0.9179   0.5877
  -3.500  -0.2152   0.01807   0.01270  -0.0645   0.9157   0.6047
  -3.250  -0.1815   0.01875   0.01344  -0.0646   0.9139   0.6161
  -3.000  -0.1613   0.01922   0.01388  -0.0631   0.9096   0.6264
  -2.750  -0.1488   0.01985   0.01457  -0.0595   0.9033   0.6326
  -2.500  -0.1189   0.02023   0.01491  -0.0597   0.8997   0.6429
  -2.250  -0.0880   0.02070   0.01543  -0.0594   0.8968   0.6491
  -2.000  -0.0550   0.02132   0.01609  -0.0592   0.8945   0.6547
  -1.750  -0.0144   0.02171   0.01648  -0.0610   0.8929   0.6641
  -1.500  -0.0154   0.02228   0.01709  -0.0555   0.8831   0.6705
  -1.250   0.0031   0.02334   0.01826  -0.0514   0.8777   0.6778
  -1.000   0.0554   0.02354   0.01846  -0.0542   0.8740   0.6912
  -0.750   0.0909   0.02336   0.01831  -0.0531   0.8644   0.6943
  -0.500   0.1401   0.02234   0.01730  -0.0539   0.8532   0.6969
  -0.250   0.1786   0.02146   0.01639  -0.0535   0.8418   0.7001
   0.000   0.2126   0.02069   0.01560  -0.0535   0.8313   0.7043
   0.250   0.2539   0.01983   0.01467  -0.0557   0.8256   0.7096
   0.500   0.2792   0.01935   0.01420  -0.0556   0.8130   0.7137
   0.750   0.3108   0.01873   0.01358  -0.0548   0.8044   0.7157
   1.000   0.3335   0.01841   0.01330  -0.0530   0.7900   0.7177
   1.250   0.3610   0.01790   0.01279  -0.0518   0.7738   0.7201
   1.500   0.3873   0.01740   0.01228  -0.0506   0.7494   0.7231
   1.750   0.4145   0.01688   0.01167  -0.0498   0.7107   0.7263
   2.000   0.4391   0.01659   0.01079  -0.0485   0.5806   0.7296
   2.250   0.4428   0.01809   0.01088  -0.0454   0.3415   0.7346
   2.500   0.4496   0.01919   0.01128  -0.0421   0.2190   0.7367
   2.750   0.4664   0.01981   0.01160  -0.0403   0.1785   0.7387
   3.000   0.4862   0.02029   0.01191  -0.0390   0.1594   0.7408
   3.250   0.5074   0.02073   0.01223  -0.0380   0.1464   0.7432
   3.500   0.5313   0.02105   0.01249  -0.0375   0.1359   0.7460
   3.750   0.5557   0.02145   0.01281  -0.0372   0.1270   0.7495
   4.000   0.5818   0.02194   0.01317  -0.0375   0.1195   0.7533
   4.250   0.6104   0.02234   0.01347  -0.0383   0.1129   0.7564
   4.500   0.6325   0.02280   0.01390  -0.0373   0.1079   0.7584
   4.750   0.6556   0.02324   0.01429  -0.0365   0.1036   0.7606
   5.000   0.6801   0.02388   0.01486  -0.0360   0.1000   0.7630
   5.250   0.7057   0.02435   0.01534  -0.0356   0.0966   0.7658
   5.500   0.7326   0.02493   0.01581  -0.0357   0.0938   0.7693
   5.750   0.7622   0.02564   0.01649  -0.0363   0.0912   0.7731
   6.000   0.7933   0.02622   0.01707  -0.0373   0.0887   0.7767
   6.250   0.8184   0.02674   0.01758  -0.0368   0.0869   0.7789
   6.500   0.8457   0.02748   0.01824  -0.0367   0.0854   0.7814
   6.750   0.8739   0.02839   0.01917  -0.0368   0.0841   0.7842
   7.000   0.9005   0.02915   0.02005  -0.0366   0.0828   0.7874
   7.250   0.9286   0.03001   0.02098  -0.0368   0.0817   0.7909
   7.500   0.9583   0.03095   0.02196  -0.0375   0.0806   0.7950
   7.750   0.9844   0.03182   0.02288  -0.0373   0.0797   0.7982
   8.000   1.0086   0.03270   0.02380  -0.0368   0.0789   0.8013
   8.250   1.0346   0.03374   0.02484  -0.0367   0.0780   0.8047
   8.500   1.0617   0.03527   0.02640  -0.0370   0.0772   0.8083
   8.750   1.0829   0.03649   0.02787  -0.0363   0.0766   0.8122
   9.000   1.1042   0.03797   0.02957  -0.0358   0.0760   0.8157
   9.250   1.1211   0.03953   0.03138  -0.0343   0.0757   0.8188
   9.500   1.1369   0.04131   0.03341  -0.0329   0.0754   0.8222
   9.750   1.1513   0.04333   0.03568  -0.0316   0.0752   0.8262
  10.000   1.1639   0.04564   0.03826  -0.0302   0.0751   0.8305
  10.250   1.1720   0.04812   0.04102  -0.0284   0.0751   0.8343
  10.500   1.1748   0.05072   0.04391  -0.0258   0.0753   0.8380
  10.750   1.1738   0.05363   0.04711  -0.0232   0.0756   0.8421
  11.000   1.1687   0.05669   0.05042  -0.0205   0.0759   0.8463
  11.250   1.1601   0.05980   0.05377  -0.0178   0.0762   0.8503
  11.500   1.1476   0.06293   0.05712  -0.0148   0.0765   0.8539
  11.750   1.1355   0.06629   0.06068  -0.0126   0.0767   0.8578
  12.000   1.1258   0.06986   0.06441  -0.0111   0.0769   0.8619
  12.250   1.1236   0.07349   0.06812  -0.0105   0.0772   0.8659
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