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LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il)
Reynolds number: 200,000
Max Cl/Cd: 57.42 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c141c-il-200000-n5.txt
Download as CSV file: xf-c141c-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL426.57 AIRFOIL                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6835   0.07915   0.07516  -0.0486   1.0000   0.0214
 -12.000  -0.7340   0.06260   0.05840  -0.0622   1.0000   0.0210
 -11.750  -0.7658   0.05538   0.05098  -0.0665   1.0000   0.0209
 -11.500  -0.7954   0.05061   0.04600  -0.0663   1.0000   0.0208
 -11.250  -0.8244   0.04743   0.04263  -0.0624   1.0000   0.0208
 -11.000  -0.8521   0.04502   0.04003  -0.0564   1.0000   0.0209
 -10.750  -0.8736   0.04220   0.03691  -0.0511   1.0000   0.0210
 -10.500  -0.8890   0.03950   0.03386  -0.0460   1.0000   0.0212
 -10.250  -0.8975   0.03702   0.03103  -0.0415   1.0000   0.0214
 -10.000  -0.8964   0.03526   0.02912  -0.0381   1.0000   0.0216
  -9.750  -0.8912   0.03387   0.02759  -0.0351   1.0000   0.0219
  -9.500  -0.8839   0.03259   0.02618  -0.0323   1.0000   0.0223
  -9.250  -0.8642   0.03107   0.02446  -0.0321   0.9982   0.0228
  -9.000  -0.8410   0.02947   0.02260  -0.0324   0.9959   0.0235
  -8.750  -0.8164   0.02789   0.02075  -0.0328   0.9939   0.0243
  -8.500  -0.7927   0.02649   0.01904  -0.0328   0.9913   0.0255
  -8.250  -0.7678   0.02515   0.01746  -0.0329   0.9888   0.0266
  -8.000  -0.7409   0.02420   0.01646  -0.0335   0.9866   0.0276
  -7.750  -0.7126   0.02330   0.01546  -0.0343   0.9847   0.0287
  -7.500  -0.6848   0.02237   0.01439  -0.0348   0.9828   0.0300
  -7.250  -0.6601   0.02149   0.01336  -0.0345   0.9796   0.0314
  -7.000  -0.6335   0.02066   0.01244  -0.0348   0.9768   0.0331
  -6.750  -0.6048   0.02010   0.01185  -0.0354   0.9744   0.0351
  -6.500  -0.5747   0.01948   0.01115  -0.0363   0.9725   0.0376
  -6.250  -0.5440   0.01878   0.01034  -0.0372   0.9709   0.0398
  -6.000  -0.5211   0.01826   0.00984  -0.0366   0.9668   0.0424
  -5.750  -0.4939   0.01782   0.00934  -0.0368   0.9636   0.0458
  -5.500  -0.4650   0.01727   0.00876  -0.0373   0.9610   0.0493
  -5.250  -0.4340   0.01684   0.00831  -0.0383   0.9590   0.0540
  -5.000  -0.4019   0.01639   0.00783  -0.0395   0.9573   0.0591
  -4.750  -0.3779   0.01602   0.00747  -0.0389   0.9531   0.0646
  -4.500  -0.3514   0.01566   0.00709  -0.0389   0.9492   0.0715
  -4.250  -0.3213   0.01531   0.00674  -0.0396   0.9464   0.0804
  -4.000  -0.2894   0.01493   0.00642  -0.0407   0.9443   0.0930
  -3.750  -0.2563   0.01457   0.00610  -0.0420   0.9426   0.1103
  -3.500  -0.2328   0.01424   0.00588  -0.0414   0.9378   0.1322
  -3.250  -0.2063   0.01388   0.00566  -0.0413   0.9336   0.1652
  -3.000  -0.1769   0.01340   0.00541  -0.0420   0.9307   0.2203
  -2.750  -0.1476   0.01275   0.00516  -0.0428   0.9283   0.3129
  -2.500  -0.1263   0.01205   0.00500  -0.0418   0.9236   0.4434
  -2.250  -0.1056   0.01146   0.00495  -0.0404   0.9185   0.5722
  -2.000  -0.0784   0.01110   0.00492  -0.0400   0.9153   0.6619
  -1.750  -0.0484   0.01088   0.00489  -0.0401   0.9129   0.7229
  -1.500  -0.0250   0.01081   0.00494  -0.0388   0.9073   0.7648
  -1.250   0.0026   0.01073   0.00494  -0.0384   0.9030   0.8004
  -1.000   0.0337   0.01067   0.00495  -0.0386   0.9000   0.8323
  -0.750   0.0673   0.01067   0.00503  -0.0390   0.8978   0.8683
  -0.500   0.0959   0.01082   0.00523  -0.0385   0.8926   0.9005
  -0.250   0.1291   0.01087   0.00528  -0.0393   0.8882   0.9176
   0.000   0.1632   0.01083   0.00522  -0.0404   0.8846   0.9274
   0.250   0.2016   0.01078   0.00515  -0.0424   0.8819   0.9341
   0.500   0.2305   0.01084   0.00521  -0.0426   0.8744   0.9437
   0.750   0.2676   0.01080   0.00518  -0.0444   0.8698   0.9501
   1.000   0.3026   0.01074   0.00512  -0.0458   0.8646   0.9574
   1.250   0.3393   0.01067   0.00506  -0.0475   0.8548   0.9626
   1.500   0.3732   0.01049   0.00487  -0.0484   0.8396   0.9688
   1.750   0.4093   0.01027   0.00461  -0.0497   0.8178   0.9727
   2.000   0.4450   0.01014   0.00446  -0.0510   0.7949   0.9769
   2.250   0.4784   0.01007   0.00435  -0.0520   0.7716   0.9822
   2.500   0.5139   0.01002   0.00423  -0.0534   0.7419   0.9858
   2.750   0.5481   0.01006   0.00414  -0.0545   0.7025   0.9897
   3.000   0.5796   0.01023   0.00410  -0.0551   0.6490   0.9942
   3.250   0.6098   0.01062   0.00413  -0.0557   0.5701   0.9982
   3.500   0.6280   0.01124   0.00428  -0.0539   0.4748   1.0000
   3.750   0.6380   0.01199   0.00455  -0.0507   0.3786   1.0000
   4.000   0.6495   0.01270   0.00486  -0.0478   0.3009   1.0000
   4.250   0.6626   0.01334   0.00520  -0.0452   0.2385   1.0000
   4.500   0.6775   0.01388   0.00551  -0.0430   0.1949   1.0000
   4.750   0.6933   0.01437   0.00584  -0.0408   0.1619   1.0000
   5.000   0.7100   0.01482   0.00616  -0.0388   0.1376   1.0000
   5.250   0.7270   0.01526   0.00652  -0.0369   0.1181   1.0000
   5.500   0.7443   0.01569   0.00688  -0.0350   0.1030   1.0000
   5.750   0.7619   0.01611   0.00726  -0.0332   0.0907   1.0000
   6.000   0.7798   0.01654   0.00766  -0.0314   0.0808   1.0000
   6.250   0.7975   0.01702   0.00812  -0.0296   0.0728   1.0000
   6.500   0.8157   0.01748   0.00857  -0.0279   0.0655   1.0000
   6.750   0.8340   0.01798   0.00907  -0.0262   0.0598   1.0000
   7.000   0.8523   0.01850   0.00958  -0.0247   0.0546   1.0000
   7.250   0.8705   0.01906   0.01018  -0.0230   0.0504   1.0000
   7.500   0.8893   0.01960   0.01076  -0.0215   0.0466   1.0000
   7.750   0.9063   0.02030   0.01143  -0.0198   0.0433   1.0000
   8.000   0.9253   0.02086   0.01208  -0.0184   0.0405   1.0000
   8.250   0.9434   0.02150   0.01278  -0.0169   0.0381   1.0000
   8.500   0.9599   0.02229   0.01357  -0.0153   0.0362   1.0000
   8.750   0.9770   0.02310   0.01446  -0.0136   0.0345   1.0000
   9.000   0.9941   0.02385   0.01530  -0.0120   0.0327   1.0000
   9.250   1.0107   0.02458   0.01609  -0.0104   0.0311   1.0000
   9.500   1.0260   0.02539   0.01694  -0.0087   0.0298   1.0000
   9.750   1.0407   0.02643   0.01803  -0.0069   0.0287   1.0000
  10.000   1.0568   0.02743   0.01918  -0.0053   0.0277   1.0000
  10.250   1.0722   0.02851   0.02038  -0.0037   0.0268   1.0000
  10.500   1.0870   0.02961   0.02160  -0.0020   0.0260   1.0000
  10.750   1.1008   0.03072   0.02282  -0.0003   0.0253   1.0000
  11.000   1.1135   0.03182   0.02400   0.0014   0.0246   1.0000
  11.250   1.1251   0.03307   0.02530   0.0031   0.0240   1.0000
  11.500   1.1357   0.03458   0.02696   0.0049   0.0233   1.0000
  11.750   1.1452   0.03610   0.02872   0.0068   0.0227   1.0000
  12.000   1.1527   0.03777   0.03062   0.0088   0.0221   1.0000
  12.250   1.1582   0.03960   0.03267   0.0108   0.0216   1.0000
  12.500   1.1617   0.04156   0.03483   0.0128   0.0212   1.0000
  12.750   1.1632   0.04365   0.03713   0.0148   0.0209   1.0000
  13.000   1.1629   0.04589   0.03957   0.0166   0.0206   1.0000
  13.250   1.1607   0.04833   0.04220   0.0182   0.0203   1.0000
  13.500   1.1569   0.05099   0.04504   0.0195   0.0201   1.0000
  13.750   1.1511   0.05394   0.04817   0.0205   0.0199   1.0000
  14.000   1.1434   0.05726   0.05168   0.0210   0.0198   1.0000
  14.250   1.1333   0.06105   0.05565   0.0210   0.0196   1.0000
  14.500   1.1209   0.06539   0.06018   0.0203   0.0195   1.0000
  14.750   1.1056   0.07049   0.06547   0.0188   0.0194   1.0000
  15.000   1.0854   0.07682   0.07202   0.0160   0.0194   1.0000
  15.250   1.0564   0.08559   0.08107   0.0111   0.0194   1.0000
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