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

LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il)
Reynolds number: 1,000,000
Max Cl/Cd: 76.43 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c141c-il-1000000-n5.txt
Download as CSV file: xf-c141c-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -1.0058   0.09309   0.09071  -0.0384   1.0000   0.0092
 -16.750  -1.1587   0.05864   0.05571  -0.0599   1.0000   0.0089
 -16.500  -1.1881   0.04954   0.04639  -0.0667   1.0000   0.0088
 -16.250  -1.2041   0.04388   0.04056  -0.0701   1.0000   0.0089
 -16.000  -1.2134   0.03983   0.03637  -0.0718   1.0000   0.0089
 -15.750  -1.2190   0.03668   0.03309  -0.0724   1.0000   0.0090
 -15.500  -1.2212   0.03419   0.03047  -0.0722   1.0000   0.0090
 -15.250  -1.2211   0.03214   0.02831  -0.0713   1.0000   0.0091
 -15.000  -1.2193   0.03043   0.02649  -0.0700   1.0000   0.0092
 -14.750  -1.2158   0.02900   0.02496  -0.0683   1.0000   0.0093
 -14.500  -1.2113   0.02780   0.02366  -0.0662   1.0000   0.0094
 -14.250  -1.2072   0.02680   0.02257  -0.0636   1.0000   0.0095
 -14.000  -1.2085   0.02601   0.02170  -0.0594   1.0000   0.0096
 -13.750  -1.2096   0.02531   0.02093  -0.0550   1.0000   0.0097
 -13.500  -1.1947   0.02441   0.01994  -0.0538   0.9989   0.0099
 -13.250  -1.1737   0.02345   0.01888  -0.0538   0.9972   0.0100
 -13.000  -1.1517   0.02252   0.01784  -0.0539   0.9957   0.0102
 -12.750  -1.1282   0.02164   0.01686  -0.0542   0.9946   0.0103
 -12.500  -1.1052   0.02083   0.01595  -0.0542   0.9930   0.0105
 -12.250  -1.0819   0.02007   0.01510  -0.0542   0.9910   0.0106
 -12.000  -1.0573   0.01937   0.01430  -0.0544   0.9893   0.0108
 -11.750  -1.0318   0.01871   0.01356  -0.0547   0.9878   0.0109
 -11.500  -1.0073   0.01788   0.01264  -0.0549   0.9862   0.0111
 -11.250  -0.9816   0.01715   0.01184  -0.0552   0.9848   0.0114
 -11.000  -0.9545   0.01654   0.01118  -0.0557   0.9835   0.0117
 -10.750  -0.9315   0.01604   0.01064  -0.0552   0.9804   0.0120
 -10.500  -0.9067   0.01556   0.01010  -0.0551   0.9777   0.0123
 -10.250  -0.8812   0.01509   0.00958  -0.0550   0.9753   0.0126
 -10.000  -0.8550   0.01464   0.00908  -0.0551   0.9731   0.0130
  -9.750  -0.8282   0.01422   0.00860  -0.0553   0.9712   0.0133
  -9.500  -0.8040   0.01386   0.00819  -0.0548   0.9681   0.0137
  -9.250  -0.7800   0.01346   0.00774  -0.0543   0.9647   0.0140
  -9.000  -0.7556   0.01303   0.00728  -0.0539   0.9614   0.0147
  -8.750  -0.7301   0.01266   0.00689  -0.0537   0.9587   0.0152
  -8.500  -0.7044   0.01233   0.00653  -0.0534   0.9560   0.0158
  -8.250  -0.6798   0.01203   0.00619  -0.0530   0.9523   0.0165
  -8.000  -0.6547   0.01175   0.00587  -0.0526   0.9487   0.0170
  -7.750  -0.6293   0.01143   0.00552  -0.0522   0.9454   0.0178
  -7.500  -0.6035   0.01113   0.00521  -0.0519   0.9424   0.0188
  -7.250  -0.5779   0.01087   0.00493  -0.0516   0.9390   0.0199
  -7.000  -0.5520   0.01064   0.00468  -0.0514   0.9351   0.0210
  -6.750  -0.5261   0.01038   0.00440  -0.0511   0.9315   0.0224
  -6.500  -0.4998   0.01013   0.00415  -0.0509   0.9284   0.0241
  -6.250  -0.4733   0.00992   0.00392  -0.0507   0.9251   0.0255
  -6.000  -0.4469   0.00971   0.00370  -0.0505   0.9212   0.0270
  -5.750  -0.4205   0.00949   0.00348  -0.0503   0.9174   0.0292
  -5.500  -0.3937   0.00930   0.00328  -0.0501   0.9139   0.0312
  -5.250  -0.3668   0.00912   0.00308  -0.0500   0.9105   0.0336
  -5.000  -0.3401   0.00892   0.00291  -0.0498   0.9065   0.0370
  -4.750  -0.3131   0.00877   0.00274  -0.0497   0.9025   0.0395
  -4.500  -0.2861   0.00858   0.00257  -0.0496   0.8989   0.0441
  -4.250  -0.2589   0.00843   0.00242  -0.0495   0.8952   0.0483
  -4.000  -0.2320   0.00826   0.00228  -0.0494   0.8909   0.0550
  -3.750  -0.2048   0.00811   0.00214  -0.0493   0.8867   0.0611
  -3.500  -0.1775   0.00797   0.00201  -0.0492   0.8828   0.0686
  -3.250  -0.1503   0.00781   0.00190  -0.0491   0.8788   0.0797
  -3.000  -0.1232   0.00766   0.00179  -0.0490   0.8743   0.0918
  -2.750  -0.0959   0.00751   0.00169  -0.0489   0.8698   0.1063
  -2.500  -0.0688   0.00735   0.00159  -0.0488   0.8657   0.1269
  -2.250  -0.0419   0.00716   0.00150  -0.0487   0.8608   0.1550
  -2.000  -0.0153   0.00695   0.00142  -0.0485   0.8555   0.1902
  -1.750   0.0111   0.00672   0.00132  -0.0483   0.8506   0.2357
  -1.500   0.0372   0.00645   0.00125  -0.0481   0.8449   0.2940
  -1.250   0.0628   0.00614   0.00116  -0.0478   0.8387   0.3654
  -1.000   0.0875   0.00575   0.00109  -0.0473   0.8326   0.4629
  -0.750   0.1128   0.00547   0.00104  -0.0469   0.8254   0.5361
  -0.500   0.1382   0.00525   0.00101  -0.0464   0.8161   0.6005
  -0.250   0.1638   0.00512   0.00098  -0.0459   0.8025   0.6461
   0.000   0.1893   0.00504   0.00097  -0.0453   0.7842   0.6838
   0.500   0.2368   0.00507   0.00098  -0.0433   0.7189   0.7567
   0.750   0.2602   0.00510   0.00103  -0.0423   0.6889   0.7978
   1.000   0.2836   0.00518   0.00109  -0.0412   0.6556   0.8281
   1.250   0.3078   0.00533   0.00116  -0.0404   0.6200   0.8448
   1.500   0.3315   0.00554   0.00125  -0.0395   0.5761   0.8595
   1.750   0.3550   0.00579   0.00135  -0.0386   0.5279   0.8742
   2.000   0.3777   0.00612   0.00149  -0.0375   0.4688   0.8884
   2.250   0.3989   0.00658   0.00167  -0.0363   0.3910   0.9023
   2.500   0.4210   0.00700   0.00186  -0.0352   0.3252   0.9159
   2.750   0.4438   0.00739   0.00204  -0.0342   0.2686   0.9290
   3.000   0.4673   0.00771   0.00221  -0.0334   0.2256   0.9407
   3.250   0.4921   0.00805   0.00239  -0.0329   0.1867   0.9487
   3.500   0.5168   0.00835   0.00256  -0.0323   0.1559   0.9565
   3.750   0.5441   0.00862   0.00273  -0.0323   0.1324   0.9623
   4.000   0.5700   0.00887   0.00290  -0.0320   0.1135   0.9688
   4.250   0.5985   0.00912   0.00307  -0.0324   0.0978   0.9730
   4.500   0.6276   0.00937   0.00326  -0.0328   0.0851   0.9771
   4.750   0.6548   0.00962   0.00345  -0.0328   0.0732   0.9820
   5.000   0.6844   0.00989   0.00366  -0.0334   0.0624   0.9848
   5.250   0.7149   0.01016   0.00388  -0.0343   0.0538   0.9871
   5.500   0.7456   0.01041   0.00410  -0.0351   0.0480   0.9894
   5.750   0.7754   0.01068   0.00433  -0.0358   0.0428   0.9919
   6.000   0.8051   0.01094   0.00457  -0.0364   0.0389   0.9942
   6.250   0.8365   0.01122   0.00483  -0.0375   0.0349   0.9957
   6.500   0.8675   0.01151   0.00510  -0.0384   0.0314   0.9975
   6.750   0.8979   0.01181   0.00538  -0.0393   0.0285   0.9993
   7.000   0.9225   0.01207   0.00565  -0.0388   0.0265   1.0000
   7.250   0.9412   0.01234   0.00590  -0.0371   0.0246   1.0000
   7.500   0.9604   0.01260   0.00617  -0.0355   0.0231   1.0000
   7.750   0.9802   0.01286   0.00644  -0.0340   0.0219   1.0000
   8.000   0.9998   0.01315   0.00674  -0.0325   0.0206   1.0000
   8.250   1.0195   0.01349   0.00708  -0.0310   0.0192   1.0000
   8.500   1.0405   0.01379   0.00739  -0.0298   0.0184   1.0000
   8.750   1.0616   0.01410   0.00773  -0.0287   0.0175   1.0000
   9.000   1.0826   0.01446   0.00810  -0.0276   0.0166   1.0000
   9.250   1.1033   0.01485   0.00850  -0.0264   0.0158   1.0000
   9.500   1.1237   0.01528   0.00895  -0.0252   0.0152   1.0000
   9.750   1.1447   0.01566   0.00936  -0.0242   0.0148   1.0000
  10.000   1.1653   0.01606   0.00981  -0.0231   0.0144   1.0000
  10.250   1.1853   0.01648   0.01027  -0.0219   0.0140   1.0000
  10.500   1.2043   0.01691   0.01073  -0.0205   0.0136   1.0000
  10.750   1.2225   0.01737   0.01123  -0.0190   0.0133   1.0000
  11.000   1.2403   0.01787   0.01177  -0.0175   0.0129   1.0000
  11.250   1.2572   0.01843   0.01236  -0.0159   0.0125   1.0000
  11.500   1.2727   0.01911   0.01309  -0.0141   0.0121   1.0000
  11.750   1.2900   0.01964   0.01367  -0.0127   0.0119   1.0000
  12.000   1.3069   0.02020   0.01429  -0.0112   0.0117   1.0000
  12.250   1.3229   0.02081   0.01497  -0.0097   0.0115   1.0000
  12.500   1.3384   0.02147   0.01569  -0.0081   0.0113   1.0000
  12.750   1.3531   0.02216   0.01646  -0.0065   0.0111   1.0000
  13.000   1.3675   0.02290   0.01726  -0.0048   0.0109   1.0000
  13.250   1.3811   0.02368   0.01810  -0.0032   0.0108   1.0000
  13.500   1.3940   0.02451   0.01900  -0.0016   0.0106   1.0000
  13.750   1.4063   0.02540   0.01996   0.0001   0.0104   1.0000
  14.000   1.4176   0.02635   0.02099   0.0017   0.0102   1.0000
  14.250   1.4280   0.02740   0.02210   0.0034   0.0101   1.0000
  14.500   1.4370   0.02856   0.02334   0.0051   0.0099   1.0000
  14.750   1.4446   0.02985   0.02472   0.0068   0.0098   1.0000
  15.000   1.4500   0.03135   0.02630   0.0086   0.0096   1.0000
  15.250   1.4519   0.03317   0.02823   0.0104   0.0094   1.0000
  15.500   1.4559   0.03489   0.03005   0.0119   0.0093   1.0000
  15.750   1.4617   0.03651   0.03176   0.0130   0.0092   1.0000
  16.000   1.4661   0.03830   0.03367   0.0141   0.0092   1.0000
  16.250   1.4684   0.04037   0.03584   0.0150   0.0091   1.0000
  16.500   1.4695   0.04265   0.03824   0.0158   0.0090   1.0000
  16.750   1.4684   0.04525   0.04095   0.0163   0.0089   1.0000
  17.000   1.4659   0.04815   0.04398   0.0165   0.0089   1.0000
  17.250   1.4618   0.05144   0.04738   0.0163   0.0088   1.0000
  17.500   1.4554   0.05519   0.05126   0.0157   0.0087   1.0000
  17.750   1.4466   0.05950   0.05571   0.0146   0.0087   1.0000
  18.000   1.4357   0.06442   0.06076   0.0130   0.0086   1.0000
  18.250   1.4208   0.07022   0.06672   0.0106   0.0086   1.0000
  18.500   1.4012   0.07715   0.07380   0.0073   0.0086   1.0000
  18.750   1.3763   0.08543   0.08226   0.0030   0.0086   1.0000
  19.000   1.3427   0.09568   0.09269  -0.0024   0.0086   1.0000
  19.250   1.2999   0.10805   0.10526  -0.0090   0.0086   1.0000
<< Back to LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il)

Polar data table (+)

Polar graphs


<< Back to LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il)