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NLR-7301 AIRFOIL (nlr7301-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NLR-7301 AIRFOIL (nlr7301-il)
Reynolds number: 50,000
Max Cl/Cd: 18.66 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlr7301-il-50000-n5.txt
Download as CSV file: xf-nlr7301-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5453   0.10946   0.10043  -0.0470   1.0000   0.0914
 -12.500  -0.6182   0.09099   0.08177  -0.0584   1.0000   0.0911
 -12.250  -0.6814   0.07901   0.06954  -0.0650   1.0000   0.0905
 -12.000  -0.7227   0.07189   0.06217  -0.0676   1.0000   0.0905
 -11.750  -0.7539   0.06682   0.05688  -0.0683   1.0000   0.0908
 -11.500  -0.7798   0.06297   0.05281  -0.0674   1.0000   0.0912
 -11.250  -0.8039   0.06004   0.04968  -0.0651   1.0000   0.0917
 -11.000  -0.8285   0.05788   0.04736  -0.0613   1.0000   0.0922
 -10.750  -0.8500   0.05586   0.04513  -0.0574   1.0000   0.0927
 -10.500  -0.8468   0.05447   0.04378  -0.0549   1.0000   0.0938
 -10.250  -0.8472   0.05311   0.04240  -0.0521   1.0000   0.0950
 -10.000  -0.8486   0.05171   0.04092  -0.0493   1.0000   0.0964
  -9.750  -0.8503   0.05021   0.03928  -0.0464   1.0000   0.0981
  -9.500  -0.8516   0.04858   0.03741  -0.0436   1.0000   0.1000
  -9.250  -0.8479   0.04703   0.03568  -0.0411   1.0000   0.1019
  -9.000  -0.8357   0.04593   0.03464  -0.0392   1.0000   0.1039
  -8.750  -0.8253   0.04477   0.03342  -0.0372   1.0000   0.1064
  -8.500  -0.8155   0.04352   0.03200  -0.0352   1.0000   0.1093
  -8.250  -0.8024   0.04240   0.03081  -0.0334   1.0000   0.1123
  -8.000  -0.7874   0.04152   0.02999  -0.0316   1.0000   0.1154
  -7.750  -0.7725   0.04058   0.02896  -0.0298   1.0000   0.1193
  -7.500  -0.7563   0.03974   0.02811  -0.0281   1.0000   0.1233
  -7.250  -0.7404   0.03902   0.02744  -0.0263   1.0000   0.1277
  -7.000  -0.7238   0.03832   0.02659  -0.0245   1.0000   0.1331
  -6.750  -0.7080   0.03767   0.02612  -0.0226   1.0000   0.1381
  -6.500  -0.6928   0.03702   0.02541  -0.0207   1.0000   0.1446
  -6.250  -0.6788   0.03634   0.02485  -0.0188   1.0000   0.1508
  -6.000  -0.6647   0.03567   0.02415  -0.0170   1.0000   0.1592
  -5.750  -0.6449   0.03487   0.02353  -0.0164   0.9979   0.1687
  -5.500  -0.6218   0.03405   0.02282  -0.0166   0.9946   0.1816
  -5.250  -0.5994   0.03315   0.02208  -0.0170   0.9917   0.1980
  -5.000  -0.5779   0.03210   0.02125  -0.0174   0.9880   0.2203
  -4.750  -0.5551   0.03085   0.02037  -0.0185   0.9842   0.2558
  -4.500  -0.5315   0.02949   0.01971  -0.0198   0.9809   0.3262
  -4.250  -0.5143   0.03009   0.02135  -0.0159   0.9777   0.4280
  -4.000  -0.4921   0.03126   0.02272  -0.0131   0.9737   0.5041
  -3.750  -0.4634   0.03187   0.02318  -0.0133   0.9695   0.5510
  -3.500  -0.4327   0.03254   0.02371  -0.0139   0.9659   0.5836
  -3.250  -0.4103   0.03334   0.02442  -0.0122   0.9617   0.6048
  -3.000  -0.3861   0.03407   0.02506  -0.0111   0.9571   0.6245
  -2.750  -0.3613   0.03518   0.02614  -0.0088   0.9529   0.6396
  -2.500  -0.3343   0.03630   0.02722  -0.0071   0.9494   0.6568
  -2.250  -0.3178   0.03707   0.02798  -0.0039   0.9440   0.6745
  -2.000  -0.2963   0.03782   0.02871  -0.0017   0.9389   0.6934
  -1.750  -0.2704   0.03847   0.02931  -0.0004   0.9345   0.7100
  -1.500  -0.2450   0.03878   0.02959   0.0008   0.9301   0.7192
  -1.250  -0.2251   0.03871   0.02949   0.0017   0.9238   0.7281
  -1.000  -0.1971   0.03857   0.02930   0.0006   0.9182   0.7365
  -0.750  -0.1648   0.03867   0.02937  -0.0001   0.9136   0.7419
  -0.500  -0.1447   0.03854   0.02922   0.0006   0.9066   0.7484
  -0.250  -0.1162   0.03837   0.02901  -0.0010   0.8995   0.7552
   0.000  -0.0828   0.03837   0.02902  -0.0022   0.8938   0.7594
   0.250  -0.0604   0.03830   0.02896  -0.0017   0.8858   0.7638
   0.500  -0.0326   0.03823   0.02890  -0.0024   0.8774   0.7687
   0.750   0.0078   0.03820   0.02888  -0.0054   0.8710   0.7735
   1.000   0.0289   0.03807   0.02878  -0.0053   0.8597   0.7778
   1.250   0.0654   0.03796   0.02873  -0.0066   0.8508   0.7810
   1.500   0.0915   0.03774   0.02858  -0.0064   0.8368   0.7849
   1.750   0.1367   0.03683   0.02771  -0.0079   0.8137   0.7882
   2.000   0.2043   0.03474   0.02565  -0.0109   0.7818   0.7906
   2.250   0.2298   0.03372   0.02467  -0.0097   0.7537   0.7949
   2.500   0.2543   0.03284   0.02388  -0.0080   0.7290   0.7985
   2.750   0.2766   0.03196   0.02309  -0.0058   0.7014   0.8019
   3.000   0.2916   0.03141   0.02264  -0.0033   0.6654   0.8057
   3.250   0.3136   0.03064   0.02193  -0.0016   0.6135   0.8095
   3.500   0.3797   0.02875   0.01884  -0.0023   0.4124   0.8119
   3.750   0.3873   0.02981   0.01904   0.0004   0.3055   0.8161
   4.000   0.3959   0.03071   0.01947   0.0029   0.2537   0.8199
   4.250   0.4109   0.03150   0.01996   0.0042   0.2224   0.8237
   4.500   0.4307   0.03222   0.02047   0.0048   0.2010   0.8274
   4.750   0.4542   0.03294   0.02100   0.0047   0.1845   0.8313
   5.000   0.4775   0.03355   0.02149   0.0051   0.1721   0.8350
   5.250   0.5015   0.03413   0.02195   0.0055   0.1616   0.8389
   5.500   0.5305   0.03471   0.02252   0.0052   0.1519   0.8431
   5.750   0.5635   0.03542   0.02312   0.0041   0.1438   0.8472
   6.000   0.5983   0.03613   0.02381   0.0028   0.1364   0.8508
   6.250   0.6303   0.03685   0.02448   0.0022   0.1307   0.8542
   6.500   0.6617   0.03764   0.02531   0.0016   0.1254   0.8582
   6.750   0.6936   0.03856   0.02608   0.0007   0.1213   0.8627
   7.000   0.7234   0.03962   0.02734   0.0001   0.1170   0.8674
   7.250   0.7502   0.04061   0.02839   0.0001   0.1141   0.8720
   7.500   0.7786   0.04173   0.02945  -0.0003   0.1117   0.8770
   7.750   0.8049   0.04318   0.03109  -0.0007   0.1092   0.8819
   8.000   0.8257   0.04454   0.03269  -0.0001   0.1068   0.8866
   8.250   0.8468   0.04586   0.03414   0.0002   0.1045   0.8919
   8.500   0.8695   0.04721   0.03552   0.0002   0.1026   0.8977
   8.750   0.8885   0.04866   0.03706   0.0008   0.1011   0.9037
   9.000   0.9006   0.05075   0.03954   0.0020   0.0999   0.9106
   9.250   0.9101   0.05291   0.04205   0.0034   0.0989   0.9175
   9.500   0.9172   0.05525   0.04470   0.0047   0.0981   0.9252
   9.750   0.9206   0.05768   0.04745   0.0062   0.0974   0.9334
  10.000   0.9197   0.06021   0.05029   0.0078   0.0967   0.9432
  10.250   0.9156   0.06299   0.05338   0.0092   0.0961   0.9564
  10.500   0.9059   0.06605   0.05674   0.0102   0.0956   0.9987
  10.750   0.8946   0.06997   0.06092   0.0102   0.0951   1.0000
  11.000   0.8745   0.07477   0.06601   0.0096   0.0948   1.0000
  11.250   0.8344   0.08202   0.07361   0.0074   0.0950   1.0000
  11.500   0.7304   0.10090   0.09305  -0.0040   0.0968   1.0000
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