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

NLR-7301 AIRFOIL (nlr7301-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NLR-7301 AIRFOIL (nlr7301-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.24 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlr7301-il-1000000-n5.txt
Download as CSV file: xf-nlr7301-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.3153   0.07902   0.07458  -0.0489   1.0000   0.0243
 -19.500  -1.3242   0.07441   0.06988  -0.0509   1.0000   0.0244
 -19.250  -1.3304   0.07023   0.06561  -0.0527   1.0000   0.0246
 -19.000  -1.3344   0.06644   0.06175  -0.0542   1.0000   0.0248
 -18.750  -1.3360   0.06306   0.05830  -0.0554   1.0000   0.0249
 -18.500  -1.3355   0.06000   0.05517  -0.0564   1.0000   0.0251
 -18.250  -1.3340   0.05709   0.05221  -0.0573   1.0000   0.0253
 -18.000  -1.3314   0.05438   0.04943  -0.0581   1.0000   0.0254
 -17.750  -1.3268   0.05197   0.04697  -0.0587   1.0000   0.0256
 -17.500  -1.3221   0.04958   0.04452  -0.0593   1.0000   0.0258
 -17.250  -1.3153   0.04748   0.04237  -0.0597   1.0000   0.0260
 -17.000  -1.3086   0.04539   0.04022  -0.0601   1.0000   0.0262
 -16.750  -1.3001   0.04354   0.03832  -0.0604   1.0000   0.0264
 -16.500  -1.2917   0.04166   0.03639  -0.0606   1.0000   0.0266
 -16.250  -1.2816   0.04001   0.03470  -0.0608   1.0000   0.0268
 -16.000  -1.2718   0.03836   0.03300  -0.0609   1.0000   0.0270
 -15.750  -1.2606   0.03688   0.03147  -0.0610   1.0000   0.0272
 -15.500  -1.2490   0.03544   0.02998  -0.0610   1.0000   0.0274
 -15.250  -1.2375   0.03404   0.02854  -0.0610   1.0000   0.0275
 -15.000  -1.2270   0.03260   0.02707  -0.0609   1.0000   0.0278
 -14.750  -1.2155   0.03123   0.02568  -0.0608   1.0000   0.0281
 -14.500  -1.2021   0.03005   0.02447  -0.0606   1.0000   0.0284
 -14.250  -1.1883   0.02890   0.02330  -0.0605   1.0000   0.0287
 -14.000  -1.1704   0.02782   0.02219  -0.0611   0.9774   0.0291
 -13.750  -1.1548   0.02685   0.02118  -0.0609   0.9610   0.0294
 -13.500  -1.1416   0.02592   0.02019  -0.0601   0.9473   0.0298
 -13.250  -1.1273   0.02505   0.01926  -0.0594   0.9357   0.0301
 -13.000  -1.1116   0.02423   0.01839  -0.0588   0.9266   0.0305
 -12.750  -1.0952   0.02343   0.01753  -0.0583   0.9179   0.0308
 -12.500  -1.0779   0.02268   0.01672  -0.0579   0.9110   0.0311
 -12.250  -1.0609   0.02183   0.01585  -0.0576   0.9047   0.0317
 -12.000  -1.0431   0.02105   0.01505  -0.0573   0.8983   0.0322
 -11.500  -1.0045   0.01967   0.01361  -0.0568   0.8878   0.0332
 -11.250  -0.9841   0.01901   0.01292  -0.0567   0.8828   0.0337
 -11.000  -0.9630   0.01841   0.01229  -0.0566   0.8776   0.0342
 -10.750  -0.9416   0.01784   0.01167  -0.0565   0.8724   0.0347
 -10.500  -0.9208   0.01727   0.01107  -0.0563   0.8681   0.0353
 -10.250  -0.8982   0.01668   0.01048  -0.0565   0.8643   0.0360
 -10.000  -0.8737   0.01613   0.00993  -0.0570   0.8604   0.0367
  -9.750  -0.8483   0.01563   0.00940  -0.0575   0.8566   0.0375
  -9.500  -0.8221   0.01517   0.00892  -0.0581   0.8530   0.0384
  -9.250  -0.7953   0.01474   0.00846  -0.0587   0.8494   0.0393
  -9.000  -0.7682   0.01428   0.00800  -0.0594   0.8465   0.0404
  -8.750  -0.7407   0.01388   0.00761  -0.0599   0.8440   0.0416
  -8.500  -0.7130   0.01354   0.00727  -0.0604   0.8411   0.0427
  -8.250  -0.6853   0.01321   0.00694  -0.0608   0.8379   0.0439
  -8.000  -0.6575   0.01288   0.00661  -0.0612   0.8346   0.0453
  -7.750  -0.6295   0.01259   0.00631  -0.0616   0.8314   0.0469
  -7.500  -0.6012   0.01232   0.00604  -0.0619   0.8284   0.0485
  -7.250  -0.5728   0.01204   0.00576  -0.0623   0.8255   0.0507
  -7.000  -0.5439   0.01178   0.00552  -0.0628   0.8236   0.0529
  -6.750  -0.5150   0.01150   0.00527  -0.0632   0.8215   0.0553
  -6.500  -0.4858   0.01127   0.00505  -0.0636   0.8191   0.0579
  -6.250  -0.4566   0.01102   0.00483  -0.0641   0.8166   0.0608
  -6.000  -0.4273   0.01080   0.00463  -0.0645   0.8139   0.0640
  -5.750  -0.3980   0.01057   0.00443  -0.0649   0.8111   0.0681
  -5.500  -0.3685   0.01037   0.00424  -0.0653   0.8084   0.0721
  -5.250  -0.3389   0.01018   0.00406  -0.0657   0.8058   0.0766
  -5.000  -0.3092   0.00998   0.00389  -0.0662   0.8032   0.0816
  -4.750  -0.2792   0.00978   0.00374  -0.0667   0.8016   0.0876
  -4.500  -0.2492   0.00958   0.00359  -0.0671   0.7997   0.0942
  -3.750  -0.1586   0.00898   0.00316  -0.0686   0.7924   0.1229
  -3.500  -0.1283   0.00876   0.00302  -0.0692   0.7902   0.1371
  -3.250  -0.0980   0.00852   0.00287  -0.0698   0.7873   0.1577
  -3.000  -0.0679   0.00825   0.00270  -0.0703   0.7817   0.1874
  -2.750  -0.0372   0.00787   0.00251  -0.0711   0.7760   0.2296
  -2.500  -0.0063   0.00742   0.00229  -0.0720   0.7685   0.2901
  -2.250   0.0244   0.00695   0.00204  -0.0729   0.7580   0.3621
  -2.000   0.0550   0.00646   0.00179  -0.0738   0.7371   0.4452
  -1.750   0.0844   0.00631   0.00169  -0.0741   0.7005   0.4971
  -1.500   0.1113   0.00650   0.00168  -0.0737   0.6354   0.5180
  -1.250   0.1353   0.00704   0.00182  -0.0730   0.5281   0.5302
  -1.000   0.1597   0.00761   0.00200  -0.0724   0.4268   0.5394
  -0.750   0.1846   0.00815   0.00218  -0.0720   0.3328   0.5477
  -0.500   0.2100   0.00865   0.00236  -0.0716   0.2492   0.5611
  -0.250   0.2365   0.00903   0.00255  -0.0714   0.1876   0.5783
   0.000   0.2639   0.00931   0.00269  -0.0712   0.1491   0.5885
   0.250   0.2922   0.00952   0.00280  -0.0712   0.1285   0.5935
   0.500   0.3207   0.00969   0.00290  -0.0712   0.1150   0.5959
   0.750   0.3493   0.00985   0.00298  -0.0712   0.1055   0.5981
   1.000   0.3780   0.01000   0.00307  -0.0712   0.0984   0.6002
   1.250   0.4067   0.01016   0.00317  -0.0712   0.0923   0.6019
   1.500   0.4354   0.01029   0.00327  -0.0712   0.0876   0.6039
   1.750   0.4640   0.01043   0.00337  -0.0712   0.0834   0.6062
   2.000   0.4925   0.01057   0.00349  -0.0712   0.0793   0.6085
   2.250   0.5209   0.01072   0.00361  -0.0711   0.0757   0.6109
   2.500   0.5492   0.01088   0.00374  -0.0710   0.0716   0.6135
   2.750   0.5774   0.01104   0.00388  -0.0710   0.0681   0.6161
   3.000   0.6054   0.01123   0.00402  -0.0709   0.0644   0.6185
   3.250   0.6335   0.01140   0.00416  -0.0708   0.0612   0.6206
   3.500   0.6612   0.01159   0.00431  -0.0706   0.0580   0.6225
   3.750   0.6889   0.01178   0.00447  -0.0705   0.0551   0.6243
   4.000   0.7164   0.01198   0.00464  -0.0703   0.0527   0.6270
   4.250   0.7439   0.01217   0.00483  -0.0701   0.0506   0.6296
   4.500   0.7710   0.01239   0.00503  -0.0699   0.0489   0.6323
   4.750   0.7982   0.01260   0.00523  -0.0696   0.0477   0.6351
   5.000   0.8252   0.01282   0.00544  -0.0694   0.0466   0.6380
   5.250   0.8520   0.01305   0.00566  -0.0691   0.0457   0.6407
   5.500   0.8785   0.01330   0.00588  -0.0688   0.0449   0.6430
   5.750   0.9047   0.01357   0.00613  -0.0684   0.0441   0.6449
   6.000   0.9309   0.01381   0.00638  -0.0680   0.0436   0.6476
   6.250   0.9571   0.01405   0.00663  -0.0676   0.0431   0.6505
   6.500   0.9830   0.01431   0.00690  -0.0672   0.0427   0.6533
   6.750   1.0086   0.01457   0.00718  -0.0668   0.0423   0.6561
   7.000   1.0339   0.01485   0.00746  -0.0662   0.0419   0.6589
   7.250   1.0588   0.01515   0.00776  -0.0657   0.0415   0.6615
   7.500   1.0834   0.01545   0.00806  -0.0651   0.0411   0.6640
   7.750   1.1077   0.01578   0.00838  -0.0644   0.0407   0.6662
   8.000   1.1315   0.01611   0.00872  -0.0637   0.0403   0.6689
   8.250   1.1547   0.01648   0.00910  -0.0629   0.0399   0.6722
   8.500   1.1769   0.01687   0.00951  -0.0620   0.0396   0.6753
   8.750   1.1978   0.01722   0.00989  -0.0608   0.0394   0.6781
   9.000   1.2186   0.01757   0.01026  -0.0596   0.0392   0.6809
   9.250   1.2399   0.01795   0.01067  -0.0585   0.0391   0.6836
   9.500   1.2611   0.01835   0.01109  -0.0575   0.0389   0.6861
   9.750   1.2818   0.01878   0.01154  -0.0564   0.0388   0.6883
  10.000   1.3022   0.01923   0.01201  -0.0553   0.0386   0.6903
  10.250   1.3222   0.01969   0.01251  -0.0542   0.0384   0.6934
  10.500   1.3418   0.02018   0.01304  -0.0530   0.0383   0.6963
  10.750   1.3609   0.02069   0.01359  -0.0518   0.0381   0.6992
  11.000   1.3796   0.02123   0.01417  -0.0506   0.0379   0.7021
  11.250   1.3979   0.02180   0.01477  -0.0494   0.0378   0.7050
  11.500   1.4157   0.02240   0.01540  -0.0482   0.0376   0.7079
  11.750   1.4332   0.02303   0.01606  -0.0470   0.0375   0.7105
  12.000   1.4501   0.02370   0.01676  -0.0457   0.0373   0.7125
  12.250   1.4667   0.02439   0.01750  -0.0444   0.0372   0.7158
  12.500   1.4828   0.02511   0.01828  -0.0432   0.0370   0.7187
  12.750   1.4983   0.02589   0.01910  -0.0419   0.0369   0.7216
  13.000   1.5134   0.02670   0.01996  -0.0406   0.0368   0.7245
  13.250   1.5276   0.02758   0.02088  -0.0393   0.0366   0.7273
  13.500   1.5415   0.02851   0.02185  -0.0380   0.0365   0.7300
  13.750   1.5545   0.02949   0.02288  -0.0367   0.0364   0.7324
  14.000   1.5667   0.03055   0.02398  -0.0354   0.0363   0.7344
  14.250   1.5785   0.03166   0.02514  -0.0341   0.0362   0.7374
  14.500   1.5890   0.03287   0.02642  -0.0328   0.0361   0.7408
  14.750   1.5991   0.03414   0.02775  -0.0316   0.0360   0.7441
  15.000   1.6074   0.03557   0.02925  -0.0303   0.0358   0.7474
  15.250   1.6150   0.03709   0.03083  -0.0290   0.0357   0.7504
  15.500   1.6212   0.03876   0.03256  -0.0278   0.0356   0.7531
  15.750   1.6262   0.04056   0.03443  -0.0266   0.0355   0.7554
  16.000   1.6304   0.04248   0.03643  -0.0256   0.0354   0.7582
  16.250   1.6365   0.04430   0.03833  -0.0247   0.0353   0.7617
  16.500   1.6430   0.04612   0.04024  -0.0240   0.0353   0.7652
  16.750   1.6484   0.04812   0.04232  -0.0234   0.0352   0.7687
  17.000   1.6529   0.05027   0.04455  -0.0229   0.0352   0.7721
  17.250   1.6572   0.05251   0.04688  -0.0225   0.0351   0.7752
  17.500   1.6597   0.05504   0.04949  -0.0223   0.0351   0.7781
  17.750   1.6609   0.05776   0.05232  -0.0223   0.0350   0.7815
  18.000   1.6607   0.06075   0.05540  -0.0224   0.0350   0.7848
  18.250   1.6598   0.06393   0.05869  -0.0228   0.0349   0.7881
  18.500   1.6575   0.06740   0.06226  -0.0234   0.0349   0.7915
  18.750   1.6536   0.07116   0.06612  -0.0242   0.0348   0.7946
  19.000   1.6480   0.07527   0.07035  -0.0253   0.0348   0.7976
  19.250   1.6409   0.07970   0.07490  -0.0268   0.0347   0.8011
<< Back to NLR-7301 AIRFOIL (nlr7301-il)

Polar data table (+)

Polar graphs


<< Back to NLR-7301 AIRFOIL (nlr7301-il)