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JN-153 AIRFOIL (jn153-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: JN-153 AIRFOIL (jn153-il)
Reynolds number: 500,000
Max Cl/Cd: 98.81 at α=11.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-jn153-il-500000.txt
Download as CSV file: xf-jn153-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: JN-153 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.1668   0.10396   0.09910  -0.0944   0.5036   0.0180
  -9.750   0.1750   0.10153   0.09669  -0.0955   0.5035   0.0183
  -9.500   0.1654   0.09782   0.09304  -0.0992   0.5035   0.0190
  -9.250   0.1774   0.09532   0.09056  -0.0993   0.5034   0.0191
  -9.000   0.1906   0.09316   0.08842  -0.0995   0.5032   0.0192
  -8.750   0.2025   0.09118   0.08645  -0.0997   0.5029   0.0195
  -8.500   0.2116   0.08906   0.08436  -0.1005   0.5026   0.0198
  -8.250   0.2200   0.08688   0.08221  -0.1012   0.5024   0.0202
  -8.000   0.2275   0.08463   0.08000  -0.1021   0.5022   0.0204
  -7.750   0.2348   0.08239   0.07779  -0.1030   0.5019   0.0208
  -7.500   0.2408   0.07999   0.07543  -0.1040   0.5018   0.0215
  -7.250   0.2313   0.07569   0.07120  -0.1080   0.5017   0.0223
  -7.000   0.2381   0.07323   0.06878  -0.1083   0.5014   0.0224
  -6.750   0.2492   0.07161   0.06719  -0.1079   0.5011   0.0226
  -6.500   0.2572   0.06973   0.06535  -0.1081   0.5007   0.0228
  -6.250   0.2634   0.06786   0.06352  -0.1082   0.5002   0.0231
  -6.000   0.2647   0.06621   0.06192  -0.1080   0.4998   0.0234
  -5.750   0.2685   0.06414   0.05990  -0.1092   0.4995   0.0236
  -5.500   0.2755   0.06162   0.05742  -0.1116   0.4992   0.0241
  -5.250   0.2848   0.05861   0.05444  -0.1153   0.4989   0.0247
  -5.000   0.2988   0.04610   0.04165  -0.1346   0.4987   0.0260
  -4.750   0.3162   0.04480   0.04041  -0.1349   0.4982   0.0262
  -4.500   0.3355   0.04329   0.03888  -0.1359   0.4977   0.0265
  -4.250   0.3571   0.04132   0.03684  -0.1377   0.4970   0.0271
  -4.000   0.3869   0.03554   0.03040  -0.1433   0.4965   0.0300
  -3.750   0.4106   0.03409   0.02899  -0.1440   0.4958   0.0304
  -3.500   0.4360   0.03293   0.02779  -0.1448   0.4952   0.0310
  -3.250   0.4671   0.03051   0.02487  -0.1467   0.4947   0.0346
  -3.000   0.4935   0.02940   0.02376  -0.1473   0.4941   0.0352
  -2.750   0.5313   0.02391   0.01721  -0.1488   0.4936   0.0227
  -2.500   0.5606   0.02289   0.01606  -0.1491   0.4929   0.0217
  -2.250   0.5904   0.02198   0.01496  -0.1493   0.4922   0.0216
  -2.000   0.6198   0.02141   0.01423  -0.1495   0.4915   0.0219
  -1.750   0.6489   0.02104   0.01375  -0.1497   0.4908   0.0221
  -1.500   0.6776   0.02077   0.01342  -0.1498   0.4901   0.0225
  -1.250   0.7054   0.02075   0.01341  -0.1501   0.4891   0.0236
  -1.000   0.7309   0.02130   0.01398  -0.1499   0.4879   0.0249
  -0.750   0.7597   0.02102   0.01371  -0.1501   0.4872   0.0256
  -0.500   0.7885   0.02074   0.01347  -0.1503   0.4863   0.0265
  -0.250   0.8170   0.02062   0.01339  -0.1505   0.4851   0.0282
   0.000   0.8456   0.02057   0.01336  -0.1508   0.4839   0.0313
   0.250   0.8744   0.02053   0.01336  -0.1510   0.4827   0.0407
   0.500   0.9058   0.01991   0.01340  -0.1524   0.4814   0.2630
   0.750   0.9353   0.01972   0.01362  -0.1531   0.4803   0.4265
   1.000   0.9643   0.01967   0.01378  -0.1534   0.4793   0.5146
   1.250   0.9935   0.01958   0.01388  -0.1537   0.4784   0.6004
   1.500   1.0219   0.01939   0.01398  -0.1538   0.4775   0.7191
   1.750   1.0353   0.01900   0.01402  -0.1503   0.4766   0.9120
   2.000   1.0639   0.01905   0.01402  -0.1504   0.4758   1.0000
   2.250   1.0933   0.01925   0.01413  -0.1508   0.4751   1.0000
   2.500   1.1222   0.01952   0.01432  -0.1512   0.4742   1.0000
   2.750   1.1495   0.02012   0.01485  -0.1513   0.4731   1.0000
   3.000   1.1742   0.02053   0.01529  -0.1511   0.4716   1.0000
   3.250   1.1998   0.02070   0.01549  -0.1509   0.4699   1.0000
   3.500   1.2255   0.02097   0.01577  -0.1508   0.4682   1.0000
   3.750   1.2520   0.02121   0.01601  -0.1509   0.4667   1.0000
   4.000   1.2794   0.02139   0.01618  -0.1510   0.4655   1.0000
   4.250   1.3074   0.02152   0.01627  -0.1512   0.4644   1.0000
   4.500   1.3363   0.02157   0.01629  -0.1515   0.4634   1.0000
   4.750   1.3653   0.02160   0.01627  -0.1518   0.4624   1.0000
   5.000   1.3947   0.02159   0.01622  -0.1521   0.4615   1.0000
   5.250   1.4242   0.02159   0.01618  -0.1526   0.4607   1.0000
   5.500   1.4534   0.02167   0.01621  -0.1530   0.4599   1.0000
   5.750   1.4819   0.02188   0.01639  -0.1533   0.4590   1.0000
   6.000   1.5066   0.02239   0.01691  -0.1532   0.4576   1.0000
   6.250   1.5261   0.02271   0.01735  -0.1522   0.4553   1.0000
   6.500   1.5492   0.02296   0.01767  -0.1518   0.4532   1.0000
   6.750   1.5752   0.02303   0.01776  -0.1518   0.4516   1.0000
   7.000   1.6029   0.02300   0.01772  -0.1520   0.4503   1.0000
   7.250   1.6310   0.02293   0.01765  -0.1522   0.4491   1.0000
   7.500   1.6597   0.02286   0.01758  -0.1526   0.4482   1.0000
   7.750   1.6889   0.02276   0.01746  -0.1530   0.4473   1.0000
   8.000   1.7185   0.02264   0.01731  -0.1534   0.4465   1.0000
   8.250   1.7485   0.02249   0.01715  -0.1540   0.4457   1.0000
   8.500   1.7796   0.02240   0.01700  -0.1547   0.4447   1.0000
   8.750   1.7912   0.02289   0.01769  -0.1527   0.4415   1.0000
   9.000   1.8115   0.02304   0.01793  -0.1519   0.4389   1.0000
   9.250   1.8375   0.02288   0.01780  -0.1518   0.4371   1.0000
   9.500   1.8665   0.02249   0.01741  -0.1521   0.4357   1.0000
   9.750   1.8965   0.02199   0.01690  -0.1526   0.4344   1.0000
  10.000   1.9268   0.02151   0.01641  -0.1531   0.4332   1.0000
  10.250   1.9571   0.02114   0.01602  -0.1536   0.4321   1.0000
  10.500   1.9655   0.02169   0.01676  -0.1512   0.4282   1.0000
  10.750   1.9846   0.02166   0.01681  -0.1501   0.4252   1.0000
  11.000   2.0084   0.02140   0.01659  -0.1497   0.4230   1.0000
  11.250   2.0333   0.02110   0.01631  -0.1494   0.4212   1.0000
  11.500   2.0583   0.02083   0.01605  -0.1492   0.4196   1.0000
  11.750   2.0569   0.02160   0.01698  -0.1452   0.4151   1.0000
  12.000   2.0695   0.02176   0.01721  -0.1432   0.4118   1.0000
  12.250   2.0888   0.02164   0.01710  -0.1422   0.4091   1.0000
  12.500   2.0981   0.02207   0.01758  -0.1400   0.4054   1.0000
  12.750   2.0990   0.02300   0.01859  -0.1371   0.4008   1.0000
  13.000   2.1079   0.02356   0.01916  -0.1354   0.3971   1.0000
  13.250   2.0994   0.02537   0.02103  -0.1325   0.3922   1.0000
  13.500   2.0781   0.02858   0.02429  -0.1297   0.3860   1.0000
  13.750   2.0342   0.03467   0.03044  -0.1274   0.3779   1.0000
  14.000   2.0145   0.03880   0.03456  -0.1261   0.3709   1.0000
  14.250   1.9481   0.04784   0.04367  -0.1241   0.3602   1.0000
  14.500   1.9679   0.04802   0.04380  -0.1238   0.3565   1.0000
  14.750   1.9126   0.05629   0.05217  -0.1225   0.3466   1.0000
  15.000   1.9323   0.05656   0.05239  -0.1223   0.3430   1.0000
  15.250   1.8948   0.06350   0.05944  -0.1219   0.3346   1.0000
  15.500   1.9063   0.06480   0.06072  -0.1217   0.3302   1.0000
  15.750   1.8971   0.06865   0.06462  -0.1217   0.3242   1.0000
  16.000   1.8886   0.07252   0.06852  -0.1217   0.3177   1.0000
  16.250   1.9120   0.07234   0.06828  -0.1216   0.3138   1.0000
  16.500   1.8798   0.07942   0.07550  -0.1220   0.3052   1.0000
  16.750   1.8949   0.08031   0.07635  -0.1220   0.3006   1.0000
  17.000   1.8754   0.08593   0.08207  -0.1225   0.2928   1.0000
  17.250   1.8834   0.08781   0.08392  -0.1226   0.2871   1.0000
  17.500   1.8695   0.09278   0.08898  -0.1232   0.2792   1.0000
  17.750   1.8746   0.09509   0.09124  -0.1235   0.2728   1.0000
  18.000   1.8660   0.09941   0.09564  -0.1241   0.2652   1.0000
  18.250   1.8690   0.10203   0.09821  -0.1244   0.2585   1.0000
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