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KC-135 BL200.76 AIRFOIL (kc135c-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: KC-135 BL200.76 AIRFOIL (kc135c-il)
Reynolds number: 50,000
Max Cl/Cd: 34.12 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-kc135c-il-50000.txt
Download as CSV file: xf-kc135c-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: KC-135 BL200.76 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4767   0.11211   0.10517  -0.0131   1.0000   0.2548
  -9.500  -0.4615   0.10846   0.10151  -0.0111   1.0000   0.2813
  -9.250  -0.4755   0.10679   0.09996  -0.0113   1.0000   0.2993
  -9.000  -0.4679   0.10398   0.09720  -0.0093   1.0000   0.3283
  -8.750  -0.4380   0.10005   0.09323  -0.0059   1.0000   0.3692
  -8.500  -0.4184   0.09687   0.09005  -0.0032   1.0000   0.4103
  -8.250  -0.4035   0.09422   0.08743  -0.0004   1.0000   0.4553
  -8.000  -0.3905   0.09191   0.08512   0.0024   1.0000   0.5002
  -7.750  -0.3568   0.08794   0.08113   0.0043   1.0000   0.5547
  -7.500  -0.3448   0.08581   0.07903   0.0068   1.0000   0.6015
  -7.250  -0.3188   0.08195   0.07517   0.0074   1.0000   0.6445
  -7.000  -0.3004   0.07802   0.07125   0.0069   1.0000   0.6648
  -6.500  -0.2914   0.07227   0.06562   0.0069   1.0000   0.6698
  -6.000  -0.3689   0.06779   0.06160   0.0068   1.0000   0.5562
  -5.750  -0.4319   0.06451   0.05869   0.0070   1.0000   0.4932
  -5.500  -0.4841   0.06131   0.05578   0.0080   1.0000   0.4632
  -5.250  -0.5311   0.05714   0.05175   0.0069   1.0000   0.4330
  -5.000  -0.5645   0.05032   0.04455  -0.0010   1.0000   0.3731
  -4.750  -0.5461   0.04443   0.03726  -0.0094   1.0000   0.2696
  -4.500  -0.5186   0.04157   0.03342  -0.0099   1.0000   0.2109
  -4.250  -0.4955   0.03947   0.03062  -0.0085   1.0000   0.1821
  -4.000  -0.4742   0.03747   0.02813  -0.0070   1.0000   0.1669
  -3.750  -0.4520   0.03595   0.02600  -0.0052   1.0000   0.1533
  -3.500  -0.4292   0.03395   0.02364  -0.0038   1.0000   0.1427
  -3.250  -0.4063   0.03254   0.02188  -0.0024   1.0000   0.1360
  -3.000  -0.3826   0.03105   0.02011  -0.0011   1.0000   0.1309
  -2.750  -0.3591   0.02984   0.01863   0.0001   1.0000   0.1298
  -2.500  -0.3353   0.02868   0.01735   0.0011   1.0000   0.1330
  -2.250  -0.3108   0.02771   0.01625   0.0023   1.0000   0.1344
  -2.000  -0.2869   0.02692   0.01535   0.0036   1.0000   0.1360
  -1.750  -0.2642   0.02623   0.01454   0.0047   1.0000   0.1408
  -1.500  -0.2460   0.02545   0.01376   0.0061   1.0000   0.1511
  -1.250  -0.2282   0.02476   0.01299   0.0076   1.0000   0.1619
  -1.000  -0.1008   0.02221   0.01357  -0.0041   1.0000   1.0000
  -0.750  -0.1023   0.02208   0.01315  -0.0005   1.0000   1.0000
  -0.500  -0.0986   0.02206   0.01284   0.0023   1.0000   1.0000
  -0.250  -0.0910   0.02215   0.01261   0.0045   1.0000   1.0000
   0.000  -0.0804   0.02233   0.01254   0.0063   1.0000   1.0000
   0.250  -0.0677   0.02258   0.01256   0.0077   1.0000   1.0000
   0.500  -0.0537   0.02289   0.01266   0.0088   1.0000   1.0000
   0.750  -0.0387   0.02325   0.01284   0.0098   1.0000   1.0000
   1.000  -0.0231   0.02366   0.01307   0.0107   1.0000   1.0000
   1.250  -0.0070   0.02411   0.01338   0.0114   1.0000   1.0000
   1.500   0.0093   0.02461   0.01376   0.0120   1.0000   1.0000
   1.750   0.0258   0.02515   0.01420   0.0126   1.0000   1.0000
   2.000   0.0424   0.02573   0.01470   0.0131   1.0000   1.0000
   2.250   0.0763   0.02682   0.01571   0.0100   0.9928   1.0000
   2.500   0.1223   0.02818   0.01705   0.0047   0.9780   1.0000
   2.750   0.1680   0.02950   0.01838  -0.0003   0.9616   1.0000
   3.000   0.2166   0.03082   0.01974  -0.0057   0.9435   1.0000
   3.250   0.2618   0.03190   0.02089  -0.0100   0.9221   1.0000
   3.500   0.3213   0.03298   0.02211  -0.0162   0.8973   1.0000
   3.750   0.3612   0.03363   0.02288  -0.0188   0.8725   1.0000
   4.000   0.4065   0.03427   0.02370  -0.0219   0.8488   1.0000
   4.250   0.4629   0.03465   0.02435  -0.0263   0.8250   1.0000
   4.500   0.5008   0.03495   0.02487  -0.0275   0.7992   1.0000
   4.750   0.5496   0.03483   0.02504  -0.0297   0.7718   1.0000
   5.000   0.6098   0.03396   0.02460  -0.0326   0.7426   1.0000
   5.250   0.6692   0.03233   0.02337  -0.0338   0.7118   1.0000
   5.500   0.7226   0.03028   0.02173  -0.0332   0.6774   1.0000
   5.750   0.7668   0.02824   0.01997  -0.0312   0.6372   1.0000
   6.000   0.7998   0.02675   0.01865  -0.0281   0.5907   1.0000
   6.250   0.8269   0.02575   0.01766  -0.0248   0.5399   1.0000
   6.500   0.8465   0.02498   0.01664  -0.0207   0.4813   1.0000
   6.750   0.8567   0.02511   0.01635  -0.0162   0.4177   1.0000
   7.000   0.8652   0.02614   0.01699  -0.0124   0.3559   1.0000
   7.250   0.8694   0.02790   0.01827  -0.0083   0.2847   1.0000
   7.500   0.8745   0.03053   0.02021  -0.0045   0.2091   1.0000
   7.750   0.8931   0.03300   0.02238  -0.0027   0.1668   1.0000
   8.000   0.9149   0.03522   0.02460  -0.0014   0.1437   1.0000
   8.250   0.9398   0.03780   0.02728  -0.0007   0.1293   1.0000
   8.500   0.9616   0.04061   0.03026   0.0003   0.1196   1.0000
   8.750   0.9830   0.04332   0.03302   0.0011   0.1107   1.0000
   9.000   0.9953   0.04695   0.03721   0.0031   0.1080   1.0000
   9.250   1.0020   0.05065   0.04146   0.0055   0.1064   1.0000
   9.500   1.0030   0.05439   0.04568   0.0080   0.1047   1.0000
   9.750   1.0004   0.05808   0.04976   0.0105   0.1032   1.0000
  10.000   0.9934   0.06191   0.05393   0.0130   0.1022   1.0000
  10.250   0.9790   0.06600   0.05834   0.0155   0.1026   1.0000
  10.500   0.9574   0.07008   0.06266   0.0181   0.1035   1.0000
  10.750   0.9311   0.07444   0.06718   0.0200   0.1054   1.0000
  11.000   0.9070   0.07928   0.07214   0.0202   0.1070   1.0000
  11.250   0.8865   0.08475   0.07767   0.0192   0.1084   1.0000
  11.500   0.8734   0.09045   0.08341   0.0178   0.1095   1.0000
  11.750   0.7707   0.11207   0.10485  -0.0007   0.1306   1.0000
  12.000   0.7711   0.11834   0.11110  -0.0024   0.1354   1.0000
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