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St. CYR 171 (Royer) (stcyr171-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: St. CYR 171 (Royer) (stcyr171-il)
Reynolds number: 100,000
Max Cl/Cd: 29.99 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-stcyr171-il-100000-n5.txt
Download as CSV file: xf-stcyr171-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: St. CYR 171 (Royer)                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.8459   0.08668   0.08054  -0.0249   1.0000   0.0449
 -13.500  -0.8873   0.07575   0.06943  -0.0319   1.0000   0.0443
 -13.250  -0.9163   0.06829   0.06179  -0.0363   1.0000   0.0443
 -13.000  -0.9379   0.06229   0.05562  -0.0397   1.0000   0.0443
 -12.750  -0.9556   0.05703   0.05019  -0.0427   1.0000   0.0444
 -12.500  -0.9708   0.05257   0.04554  -0.0447   1.0000   0.0447
 -12.250  -0.9827   0.04903   0.04181  -0.0451   1.0000   0.0449
 -12.000  -0.9913   0.04623   0.03883  -0.0440   1.0000   0.0453
 -11.750  -0.9968   0.04396   0.03638  -0.0420   1.0000   0.0456
 -11.500  -1.0000   0.04202   0.03424  -0.0394   1.0000   0.0460
 -11.250  -0.9990   0.04022   0.03233  -0.0369   1.0000   0.0465
 -11.000  -0.9952   0.03858   0.03064  -0.0346   1.0000   0.0472
 -10.750  -0.9895   0.03708   0.02908  -0.0324   1.0000   0.0481
 -10.500  -0.9818   0.03569   0.02760  -0.0303   1.0000   0.0492
 -10.250  -0.9725   0.03436   0.02618  -0.0282   1.0000   0.0506
 -10.000  -0.9618   0.03309   0.02479  -0.0261   1.0000   0.0519
  -9.750  -0.9502   0.03188   0.02342  -0.0240   1.0000   0.0533
  -9.500  -0.9376   0.03074   0.02213  -0.0219   1.0000   0.0545
  -9.250  -0.9250   0.02962   0.02096  -0.0198   1.0000   0.0559
  -9.000  -0.9113   0.02857   0.01987  -0.0179   1.0000   0.0577
  -8.750  -0.8963   0.02761   0.01884  -0.0160   1.0000   0.0601
  -8.500  -0.8803   0.02672   0.01786  -0.0141   1.0000   0.0632
  -8.250  -0.8640   0.02585   0.01698  -0.0123   1.0000   0.0678
  -8.000  -0.8466   0.02507   0.01617  -0.0106   1.0000   0.0758
  -7.750  -0.8286   0.02435   0.01551  -0.0091   1.0000   0.0863
  -7.500  -0.8093   0.02378   0.01495  -0.0076   1.0000   0.0991
  -7.250  -0.7889   0.02331   0.01445  -0.0063   1.0000   0.1110
  -7.000  -0.7679   0.02291   0.01393  -0.0050   1.0000   0.1215
  -6.750  -0.7468   0.02255   0.01351  -0.0038   1.0000   0.1310
  -6.500  -0.7259   0.02219   0.01310  -0.0025   1.0000   0.1389
  -6.250  -0.7046   0.02188   0.01274  -0.0013   1.0000   0.1479
  -6.000  -0.6837   0.02155   0.01233   0.0001   1.0000   0.1551
  -5.750  -0.6634   0.02125   0.01204   0.0015   1.0000   0.1617
  -5.500  -0.6422   0.02097   0.01167   0.0028   1.0000   0.1692
  -5.250  -0.6220   0.02068   0.01142   0.0043   1.0000   0.1751
  -5.000  -0.6016   0.02042   0.01114   0.0058   1.0000   0.1804
  -4.750  -0.5809   0.02017   0.01084   0.0072   1.0000   0.1867
  -4.500  -0.5607   0.01994   0.01066   0.0086   1.0000   0.1943
  -4.250  -0.5398   0.01973   0.01044   0.0099   1.0000   0.2041
  -4.000  -0.5198   0.01953   0.01027   0.0114   1.0000   0.2126
  -3.750  -0.4994   0.01935   0.01006   0.0128   1.0000   0.2218
  -3.500  -0.4802   0.01917   0.00993   0.0144   1.0000   0.2293
  -3.250  -0.4607   0.01902   0.00978   0.0159   1.0000   0.2373
  -3.000  -0.4411   0.01890   0.00968   0.0174   0.9996   0.2456
  -2.750  -0.4023   0.01881   0.00960   0.0150   0.9915   0.2591
  -2.500  -0.3653   0.01871   0.00954   0.0130   0.9826   0.2739
  -2.250  -0.3299   0.01867   0.00962   0.0114   0.9725   0.2896
  -2.000  -0.2941   0.01892   0.01013   0.0099   0.9621   0.3088
  -1.750  -0.2566   0.01989   0.01161   0.0087   0.9518   0.3332
  -1.500  -0.2161   0.02136   0.01274   0.0066   0.9396   0.4169
  -1.250  -0.1779   0.02205   0.01335   0.0050   0.9297   0.4296
  -1.000  -0.1403   0.02248   0.01372   0.0034   0.9177   0.4408
  -0.750  -0.1020   0.02236   0.01358   0.0018   0.9007   0.4502
  -0.500  -0.0610   0.02208   0.01325  -0.0003   0.8781   0.4593
  -0.250  -0.0239   0.02177   0.01287  -0.0015   0.8509   0.4681
   0.000   0.0121   0.02148   0.01248  -0.0027   0.8233   0.4773
   0.250   0.0449   0.02100   0.01187  -0.0032   0.7936   0.4879
   0.500   0.0751   0.02053   0.01125  -0.0033   0.7631   0.4997
   0.750   0.1019   0.01998   0.01058  -0.0029   0.7342   0.5099
   1.000   0.1284   0.01956   0.01005  -0.0024   0.7067   0.5177
   1.250   0.1542   0.01938   0.00978  -0.0016   0.6760   0.5221
   1.500   0.1792   0.01918   0.00950  -0.0008   0.6402   0.5253
   1.750   0.2039   0.01906   0.00927   0.0002   0.5974   0.5277
   2.000   0.2283   0.01917   0.00915   0.0013   0.5500   0.5292
   2.250   0.2517   0.01941   0.00914   0.0025   0.4974   0.5307
   2.500   0.2741   0.01950   0.00901   0.0037   0.4271   0.5325
   2.750   0.2947   0.01979   0.00890   0.0051   0.3482   0.5342
   3.000   0.3166   0.02015   0.00898   0.0062   0.3063   0.5360
   3.250   0.3398   0.02048   0.00918   0.0070   0.2805   0.5375
   3.500   0.3633   0.02085   0.00943   0.0079   0.2621   0.5388
   4.000   0.4113   0.02122   0.00975   0.0094   0.2370   0.5411
   4.250   0.4350   0.02149   0.00995   0.0101   0.2285   0.5427
   4.500   0.4600   0.02170   0.01022   0.0108   0.2203   0.5445
   4.750   0.4843   0.02205   0.01054   0.0114   0.2130   0.5459
   5.000   0.5088   0.02244   0.01094   0.0121   0.2058   0.5468
   5.250   0.5335   0.02275   0.01130   0.0127   0.1972   0.5471
   5.500   0.5575   0.02314   0.01165   0.0134   0.1893   0.5469
   5.750   0.5823   0.02340   0.01204   0.0140   0.1807   0.5463
   6.000   0.6062   0.02377   0.01243   0.0146   0.1739   0.5457
   6.250   0.6307   0.02413   0.01290   0.0152   0.1673   0.5451
   6.500   0.6547   0.02444   0.01331   0.0159   0.1599   0.5444
   6.750   0.6777   0.02484   0.01374   0.0167   0.1533   0.5438
   7.000   0.7014   0.02509   0.01419   0.0175   0.1443   0.5431
   7.250   0.7234   0.02540   0.01452   0.0184   0.1358   0.5424
   7.500   0.7467   0.02570   0.01502   0.0192   0.1259   0.5417
   7.750   0.7686   0.02608   0.01549   0.0201   0.1166   0.5410
   8.000   0.7900   0.02649   0.01600   0.0212   0.1056   0.5403
   8.250   0.8111   0.02705   0.01665   0.0222   0.0933   0.5396
   8.500   0.8308   0.02774   0.01740   0.0235   0.0824   0.5389
   8.750   0.8491   0.02848   0.01815   0.0248   0.0747   0.5384
   9.000   0.8672   0.02928   0.01905   0.0261   0.0685   0.5378
   9.250   0.8835   0.03017   0.01997   0.0276   0.0644   0.5372
   9.500   0.9000   0.03110   0.02105   0.0290   0.0610   0.5366
   9.750   0.9150   0.03208   0.02215   0.0306   0.0586   0.5360
  10.000   0.9283   0.03312   0.02327   0.0324   0.0568   0.5354
  10.250   0.9392   0.03431   0.02450   0.0344   0.0553   0.5348
  10.500   0.9513   0.03554   0.02595   0.0362   0.0541   0.5341
  10.750   0.9617   0.03682   0.02742   0.0382   0.0529   0.5335
  11.000   0.9684   0.03813   0.02890   0.0406   0.0515   0.5329
  11.250   0.9731   0.03944   0.03035   0.0431   0.0503   0.5323
  11.500   0.9768   0.04090   0.03193   0.0454   0.0492   0.5318
  11.750   0.9796   0.04248   0.03360   0.0475   0.0481   0.5312
  12.000   0.9819   0.04418   0.03541   0.0493   0.0474   0.5307
  12.250   0.9834   0.04611   0.03747   0.0508   0.0467   0.5302
  12.500   0.9830   0.04838   0.03986   0.0520   0.0462   0.5298
  12.750   0.9774   0.05102   0.04275   0.0529   0.0458   0.5293
  13.000   0.9687   0.05413   0.04610   0.0532   0.0455   0.5289
  13.250   0.9565   0.05784   0.05006   0.0526   0.0451   0.5286
  13.500   0.9402   0.06241   0.05486   0.0509   0.0448   0.5283
  13.750   0.9198   0.06806   0.06073   0.0480   0.0448   0.5280
  14.000   0.8924   0.07548   0.06837   0.0434   0.0449   0.5278
  14.250   0.8514   0.08636   0.07945   0.0360   0.0453   0.5279
  14.500   0.7664   0.10842   0.10170   0.0218   0.0461   0.5287
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