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

TRAINER60 (trainer60-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: TRAINER60 (trainer60-il)
Reynolds number: 1,000,000
Max Cl/Cd: 79.28 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-trainer60-il-1000000-n5.txt
Download as CSV file: xf-trainer60-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TRAINER60                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -19.000  -1.4056   0.10278   0.09842   0.0236   0.9985   0.0204
 -18.750  -1.4191   0.09664   0.09218   0.0206   0.9981   0.0206
 -18.500  -1.4317   0.09085   0.08628   0.0180   0.9976   0.0207
 -18.250  -1.4433   0.08528   0.08062   0.0155   0.9972   0.0209
 -18.000  -1.4542   0.07993   0.07517   0.0132   0.9968   0.0212
 -17.750  -1.4621   0.07508   0.07023   0.0112   0.9964   0.0214
 -17.500  -1.4687   0.07045   0.06551   0.0092   0.9960   0.0216
 -17.250  -1.4743   0.06597   0.06094   0.0073   0.9955   0.0218
 -17.000  -1.4779   0.06182   0.05671   0.0055   0.9951   0.0221
 -16.750  -1.4819   0.05787   0.05267   0.0042   0.9946   0.0223
 -16.250  -1.5169   0.05135   0.04602   0.0092   0.9598   0.0226
 -16.000  -1.5103   0.04795   0.04252   0.0067   0.9494   0.0230
 -15.500  -1.4978   0.04200   0.03638   0.0035   0.9414   0.0236
 -15.250  -1.4912   0.03906   0.03337   0.0019   0.9386   0.0242
 -15.000  -1.4807   0.03639   0.03062   0.0001   0.9361   0.0247
 -14.750  -1.4642   0.03390   0.02806  -0.0025   0.9350   0.0253
 -14.500  -1.4320   0.03152   0.02561  -0.0077   0.9359   0.0260
 -14.250  -1.4005   0.02950   0.02353  -0.0122   0.9352   0.0268
 -14.000  -1.3759   0.02781   0.02177  -0.0150   0.9324   0.0274
 -13.750  -1.3592   0.02617   0.02007  -0.0162   0.9298   0.0282
 -13.500  -1.3416   0.02475   0.01861  -0.0171   0.9270   0.0291
 -13.250  -1.3211   0.02353   0.01733  -0.0182   0.9241   0.0300
 -13.000  -1.2975   0.02247   0.01621  -0.0196   0.9217   0.0311
 -12.750  -1.2802   0.02144   0.01515  -0.0196   0.9182   0.0320
 -12.500  -1.2609   0.02052   0.01420  -0.0197   0.9145   0.0334
 -12.250  -1.2387   0.01976   0.01340  -0.0200   0.9112   0.0348
 -12.000  -1.2209   0.01910   0.01271  -0.0191   0.9083   0.0361
 -11.750  -1.2061   0.01846   0.01206  -0.0175   0.9048   0.0379
 -11.500  -1.1891   0.01792   0.01150  -0.0160   0.9008   0.0398
 -11.250  -1.1705   0.01738   0.01094  -0.0149   0.8971   0.0422
 -11.000  -1.1539   0.01689   0.01045  -0.0131   0.8926   0.0448
 -10.750  -1.1365   0.01637   0.00994  -0.0115   0.8867   0.0483
 -10.500  -1.1172   0.01591   0.00948  -0.0102   0.8809   0.0518
 -10.000  -1.0815   0.01494   0.00854  -0.0068   0.8619   0.0630
  -9.750  -1.0645   0.01443   0.00805  -0.0049   0.8453   0.0710
  -9.500  -1.0477   0.01391   0.00750  -0.0028   0.8086   0.0825
  -9.250  -1.0244   0.01336   0.00690  -0.0024   0.7665   0.0995
  -9.000  -0.9989   0.01290   0.00646  -0.0022   0.7388   0.1157
  -8.750  -0.9726   0.01258   0.00613  -0.0021   0.7200   0.1268
  -8.500  -0.9461   0.01231   0.00585  -0.0019   0.7036   0.1356
  -8.250  -0.9197   0.01207   0.00559  -0.0016   0.6916   0.1428
  -8.000  -0.8928   0.01187   0.00537  -0.0014   0.6799   0.1493
  -7.750  -0.8659   0.01168   0.00516  -0.0012   0.6708   0.1538
  -7.500  -0.8392   0.01149   0.00496  -0.0009   0.6613   0.1591
  -7.250  -0.8119   0.01135   0.00478  -0.0007   0.6523   0.1641
  -7.000  -0.7852   0.01115   0.00459  -0.0004   0.6463   0.1692
  -6.750  -0.7586   0.01096   0.00441   0.0000   0.6397   0.1760
  -6.500  -0.7316   0.01080   0.00424   0.0003   0.6328   0.1826
  -6.250  -0.7054   0.01059   0.00405   0.0007   0.6264   0.1916
  -6.000  -0.6779   0.01045   0.00391   0.0009   0.6201   0.1969
  -5.750  -0.6512   0.01027   0.00374   0.0013   0.6125   0.2032
  -5.500  -0.6239   0.01015   0.00359   0.0016   0.6045   0.2084
  -5.250  -0.5961   0.01003   0.00346   0.0018   0.5989   0.2129
  -5.000  -0.5691   0.00987   0.00331   0.0021   0.5918   0.2202
  -4.750  -0.5417   0.00975   0.00318   0.0024   0.5840   0.2269
  -4.500  -0.5144   0.00960   0.00305   0.0027   0.5772   0.2354
  -4.250  -0.4873   0.00945   0.00292   0.0030   0.5683   0.2477
  -4.000  -0.4604   0.00930   0.00279   0.0034   0.5583   0.2613
  -3.750  -0.4332   0.00913   0.00267   0.0037   0.5492   0.2763
  -3.500  -0.4058   0.00901   0.00257   0.0040   0.5389   0.2907
  -3.250  -0.3780   0.00891   0.00249   0.0042   0.5304   0.3045
  -3.000  -0.3502   0.00881   0.00241   0.0044   0.5205   0.3179
  -2.750  -0.3221   0.00874   0.00234   0.0046   0.5113   0.3291
  -2.500  -0.2937   0.00867   0.00229   0.0047   0.5026   0.3404
  -2.250  -0.2654   0.00864   0.00224   0.0048   0.4924   0.3488
  -2.000  -0.2368   0.00859   0.00220   0.0049   0.4832   0.3573
  -1.500  -0.1797   0.00858   0.00213   0.0051   0.4589   0.3709
  -1.250  -0.1514   0.00859   0.00211   0.0052   0.4467   0.3781
  -1.000  -0.1223   0.00858   0.00209   0.0052   0.4390   0.3839
  -0.750  -0.0936   0.00857   0.00207   0.0052   0.4293   0.3917
  -0.500  -0.0648   0.00857   0.00206   0.0052   0.4203   0.3999
  -0.250  -0.0358   0.00859   0.00206   0.0052   0.4111   0.4056
   0.000  -0.0069   0.00859   0.00206   0.0052   0.4037   0.4127
   0.250   0.0226   0.00857   0.00206   0.0051   0.3987   0.4204
   0.750   0.0811   0.00858   0.00209   0.0050   0.3833   0.4412
   1.000   0.1109   0.00857   0.00211   0.0048   0.3786   0.4517
   1.250   0.1409   0.00856   0.00214   0.0045   0.3723   0.4658
   1.500   0.1705   0.00858   0.00218   0.0044   0.3641   0.4781
   1.750   0.2005   0.00860   0.00223   0.0041   0.3575   0.4923
   2.000   0.2308   0.00862   0.00228   0.0038   0.3497   0.5047
   2.250   0.2603   0.00869   0.00234   0.0036   0.3413   0.5141
   2.500   0.2907   0.00872   0.00240   0.0033   0.3341   0.5224
   2.750   0.3203   0.00881   0.00247   0.0031   0.3231   0.5298
   3.000   0.3499   0.00891   0.00253   0.0029   0.3111   0.5351
   3.250   0.3793   0.00904   0.00262   0.0027   0.2949   0.5410
   3.500   0.4087   0.00919   0.00273   0.0025   0.2777   0.5479
   3.750   0.4376   0.00938   0.00285   0.0024   0.2595   0.5540
   4.000   0.4662   0.00958   0.00299   0.0023   0.2438   0.5586
   4.250   0.4959   0.00975   0.00313   0.0020   0.2308   0.5639
   4.500   0.5262   0.00990   0.00326   0.0015   0.2213   0.5693
   4.750   0.5561   0.01008   0.00342   0.0012   0.2121   0.5745
   5.000   0.5864   0.01021   0.00355   0.0008   0.2062   0.5791
   5.250   0.6159   0.01042   0.00372   0.0005   0.1969   0.5836
   5.500   0.6479   0.01056   0.00387  -0.0003   0.1899   0.5895
   5.750   0.6801   0.01074   0.00404  -0.0013   0.1821   0.5959
   6.000   0.7122   0.01091   0.00421  -0.0022   0.1769   0.6011
   6.250   0.7439   0.01105   0.00436  -0.0029   0.1726   0.6055
   6.500   0.7767   0.01126   0.00455  -0.0040   0.1654   0.6117
   6.750   0.8098   0.01141   0.00474  -0.0052   0.1606   0.6187
   7.000   0.8418   0.01160   0.00493  -0.0061   0.1547   0.6264
   7.250   0.8743   0.01183   0.00516  -0.0071   0.1480   0.6351
   7.500   0.9072   0.01203   0.00538  -0.0083   0.1414   0.6447
   7.750   0.9400   0.01227   0.00564  -0.0094   0.1350   0.6568
   8.000   0.9741   0.01252   0.00591  -0.0109   0.1273   0.6723
   8.250   1.0092   0.01280   0.00622  -0.0127   0.1189   0.6935
   8.500   1.0473   0.01321   0.00666  -0.0152   0.1049   0.7258
   8.750   1.0776   0.01380   0.00720  -0.0162   0.0856   0.7551
   9.000   1.1033   0.01451   0.00787  -0.0163   0.0665   0.7798
   9.250   1.1282   0.01511   0.00847  -0.0162   0.0557   0.8016
   9.500   1.1526   0.01559   0.00899  -0.0158   0.0500   0.8222
   9.750   1.1749   0.01605   0.00949  -0.0149   0.0460   0.8424
  10.000   1.1962   0.01650   0.00997  -0.0138   0.0434   0.8582
  10.250   1.2184   0.01697   0.01045  -0.0129   0.0412   0.8690
  10.500   1.2391   0.01747   0.01096  -0.0119   0.0393   0.8764
  10.750   1.2614   0.01794   0.01144  -0.0111   0.0378   0.8829
  11.000   1.2823   0.01846   0.01198  -0.0102   0.0364   0.8876
  11.250   1.3020   0.01906   0.01258  -0.0091   0.0349   0.8927
  11.500   1.3223   0.01960   0.01314  -0.0081   0.0340   0.8977
  11.750   1.3422   0.02019   0.01376  -0.0072   0.0330   0.9006
  12.000   1.3609   0.02083   0.01443  -0.0062   0.0322   0.9038
  12.250   1.3767   0.02156   0.01517  -0.0048   0.0314   0.9071
  12.500   1.3851   0.02238   0.01603  -0.0023   0.0307   0.9103
  12.750   1.3968   0.02325   0.01695  -0.0008   0.0303   0.9127
  13.000   1.4081   0.02428   0.01805   0.0004   0.0299   0.9160
  13.250   1.4186   0.02545   0.01926   0.0014   0.0294   0.9193
  13.500   1.4291   0.02677   0.02063   0.0021   0.0289   0.9218
  13.750   1.4408   0.02822   0.02214   0.0023   0.0285   0.9247
  14.000   1.4505   0.02988   0.02386   0.0024   0.0280   0.9278
  14.250   1.4586   0.03177   0.02580   0.0024   0.0276   0.9300
  14.500   1.4657   0.03390   0.02799   0.0022   0.0272   0.9315
  14.750   1.4720   0.03629   0.03044   0.0015   0.0267   0.9330
  15.000   1.4791   0.03857   0.03280   0.0010   0.0265   0.9352
  15.250   1.4840   0.04106   0.03537   0.0004   0.0263   0.9381
  15.500   1.4880   0.04362   0.03801  -0.0001   0.0260   0.9408
  15.750   1.4923   0.04641   0.04088  -0.0011   0.0257   0.9433
  16.000   1.4934   0.04950   0.04405  -0.0021   0.0253   0.9454
  16.250   1.4924   0.05282   0.04746  -0.0030   0.0251   0.9470
  16.500   1.4895   0.05642   0.05114  -0.0041   0.0248   0.9484
  17.000   1.4811   0.06437   0.05927  -0.0070   0.0245   0.9510
  17.250   1.4762   0.06872   0.06372  -0.0088   0.0243   0.9525
  17.500   1.4700   0.07355   0.06865  -0.0111   0.0240   0.9543
  17.750   1.4621   0.07864   0.07385  -0.0135   0.0238   0.9557
  18.000   1.4530   0.08393   0.07925  -0.0160   0.0236   0.9566
  18.500   1.4311   0.09551   0.09104  -0.0219   0.0233   0.9604
  18.750   1.4190   0.10195   0.09759  -0.0256   0.0231   0.9629
  19.000   1.3771   0.10456   0.10021  -0.0174   0.0232   0.9941
<< Back to TRAINER60 (trainer60-il)

Polar data table (+)

Polar graphs


<< Back to TRAINER60 (trainer60-il)