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UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il)
Reynolds number: 500,000
Max Cl/Cd: 65.03 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ua79sf18-il-500000.txt
Download as CSV file: xf-ua79sf18-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: UNIVERSITY OF ALBERTA UA 79-SF-187 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.0259   0.09544   0.09213  -0.1476   0.8033   0.0161
 -12.000  -0.0278   0.09120   0.08792  -0.1493   0.8029   0.0166
 -11.750  -0.0311   0.08669   0.08345  -0.1513   0.8025   0.0169
 -11.500  -0.0365   0.08168   0.07847  -0.1537   0.8021   0.0171
 -11.250  -0.0474   0.07486   0.07170  -0.1575   0.8016   0.0172
 -11.000  -0.0701   0.06733   0.06414  -0.1621   0.8010   0.0168
 -10.750  -0.0932   0.06233   0.05907  -0.1640   0.8002   0.0166
 -10.500  -0.1151   0.05842   0.05509  -0.1643   0.7993   0.0167
 -10.250  -0.1340   0.05531   0.05190  -0.1637   0.7986   0.0166
 -10.000  -0.1523   0.05257   0.04907  -0.1622   0.7979   0.0165
  -9.750  -0.1690   0.05019   0.04659  -0.1600   0.7970   0.0169
  -9.500  -0.1844   0.04811   0.04439  -0.1570   0.7961   0.0173
  -9.250  -0.1991   0.04663   0.04279  -0.1531   0.7953   0.0175
  -9.000  -0.2121   0.04550   0.04155  -0.1486   0.7944   0.0179
  -6.750  -0.1684   0.02743   0.02151  -0.1236   0.7849   0.0141
  -6.500  -0.1390   0.02528   0.01919  -0.1234   0.7844   0.0107
  -6.250  -0.1122   0.02331   0.01703  -0.1229   0.7839   0.0097
  -6.000  -0.0920   0.02235   0.01597  -0.1216   0.7833   0.0094
  -5.750  -0.0758   0.02168   0.01523  -0.1198   0.7826   0.0095
  -5.500  -0.0611   0.02127   0.01475  -0.1178   0.7819   0.0097
  -5.250  -0.0813   0.02236   0.01593  -0.1104   0.7753   0.0099
  -5.000  -0.0708   0.02211   0.01563  -0.1077   0.7733   0.0104
  -4.750  -0.0549   0.02175   0.01521  -0.1060   0.7720   0.0111
  -4.500  -0.0353   0.02137   0.01477  -0.1048   0.7712   0.0118
  -4.250  -0.0121   0.02110   0.01444  -0.1043   0.7705   0.0127
  -4.000  -0.0552   0.02290   0.01627  -0.0928   0.7612   0.0124
  -3.750  -0.0370   0.02254   0.01583  -0.0915   0.7595   0.0153
  -3.500  -0.0094   0.02212   0.01535  -0.0917   0.7586   0.0183
  -3.250   0.0119   0.02083   0.01460  -0.0912   0.7578   0.1558
  -3.000  -0.0104   0.02112   0.01531  -0.0834   0.7510   0.2623
  -2.750   0.0223   0.01950   0.01495  -0.0851   0.7523   0.6325
  -2.500   0.0851   0.01919   0.01462  -0.0906   0.7562   0.6689
  -2.250   0.0357   0.02086   0.01624  -0.0782   0.7444   0.6621
  -2.000   0.0627   0.02123   0.01673  -0.0774   0.7438   0.6917
  -1.750   0.0405   0.02289   0.01842  -0.0697   0.7355   0.6985
  -1.500   0.0636   0.02314   0.01869  -0.0688   0.7337   0.7108
  -1.250   0.0911   0.02325   0.01874  -0.0689   0.7326   0.7183
  -1.000   0.1198   0.02326   0.01873  -0.0692   0.7319   0.7225
  -0.750   0.1499   0.02323   0.01865  -0.0699   0.7312   0.7250
  -0.500   0.1816   0.02316   0.01851  -0.0708   0.7307   0.7277
  -0.250   0.2144   0.02305   0.01833  -0.0720   0.7303   0.7299
   0.000   0.2477   0.02291   0.01813  -0.0733   0.7299   0.7312
   0.250   0.2813   0.02271   0.01789  -0.0746   0.7296   0.7319
   0.500   0.3166   0.02244   0.01758  -0.0762   0.7294   0.7323
   0.750   0.3534   0.02208   0.01718  -0.0780   0.7292   0.7326
   1.000   0.3909   0.02167   0.01673  -0.0799   0.7290   0.7330
   1.250   0.4282   0.02127   0.01632  -0.0818   0.7288   0.7335
   1.500   0.3795   0.02352   0.01857  -0.0703   0.7131   0.7347
   1.750   0.4205   0.02305   0.01808  -0.0727   0.7143   0.7349
   2.000   0.4594   0.02264   0.01766  -0.0748   0.7149   0.7351
   2.250   0.4973   0.02226   0.01727  -0.0768   0.7154   0.7356
   2.500   0.5357   0.02180   0.01682  -0.0788   0.7157   0.7366
   2.750   0.5755   0.02121   0.01623  -0.0810   0.7159   0.7375
   3.750   0.7383   0.01838   0.01346  -0.0904   0.7158   0.7387
   4.000   0.7825   0.01766   0.01277  -0.0934   0.7160   0.7388
   4.250   0.7381   0.01981   0.01492  -0.0823   0.7013   0.7393
   4.500   0.7756   0.01924   0.01439  -0.0841   0.7015   0.7395
   4.750   0.8138   0.01858   0.01377  -0.0860   0.7016   0.7397
   6.000   0.9457   0.01546   0.01067  -0.0850   0.6486   0.7412
   6.250   0.9644   0.01483   0.00950  -0.0827   0.5656   0.7415
   6.500   0.9597   0.01593   0.01042  -0.0781   0.5368   0.7419
   6.750   0.9321   0.01799   0.01214  -0.0701   0.4778   0.7424
   7.000   0.9055   0.02024   0.01401  -0.0627   0.4182   0.7430
   7.250   0.8941   0.02204   0.01551  -0.0578   0.3664   0.7436
   7.500   0.8822   0.02400   0.01710  -0.0531   0.3032   0.7440
   7.750   0.8707   0.02606   0.01866  -0.0487   0.2230   0.7444
   8.000   0.8623   0.02807   0.02018  -0.0449   0.1419   0.7448
   8.250   0.8411   0.03103   0.02239  -0.0396   0.0117   0.7451
   8.500   0.8587   0.03167   0.02309  -0.0390   0.0090   0.7457
   8.750   0.8753   0.03241   0.02389  -0.0382   0.0080   0.7462
   9.000   0.8913   0.03320   0.02477  -0.0374   0.0075   0.7469
   9.250   0.9064   0.03406   0.02573  -0.0365   0.0069   0.7476
   9.500   0.9220   0.03489   0.02667  -0.0357   0.0069   0.7483
   9.750   0.9366   0.03582   0.02769  -0.0348   0.0069   0.7491
  10.000   0.9501   0.03685   0.02882  -0.0338   0.0069   0.7499
  10.250   0.9638   0.03787   0.02993  -0.0329   0.0070   0.7510
  10.500   0.9759   0.03905   0.03120  -0.0318   0.0071   0.7520
  10.750   0.9867   0.04035   0.03260  -0.0307   0.0073   0.7530
  11.000   0.9953   0.04187   0.03422  -0.0294   0.0075   0.7543
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