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 BL0 AIRFOIL (c141a-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-141 BL0 AIRFOIL (c141a-il)
Reynolds number: 200,000
Max Cl/Cd: 62.03 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c141a-il-200000.txt
Download as CSV file: xf-c141a-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL0 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.4341   0.12258   0.11884  -0.0452   1.0000   0.0788
 -12.750  -0.4439   0.11720   0.11349  -0.0461   1.0000   0.0794
 -12.500  -0.8075   0.06345   0.05874  -0.0729   1.0000   0.0437
 -12.250  -0.8327   0.06009   0.05528  -0.0703   1.0000   0.0436
 -12.000  -0.8591   0.05745   0.05253  -0.0661   1.0000   0.0434
 -11.750  -0.8874   0.05546   0.05043  -0.0603   1.0000   0.0434
 -11.500  -0.9161   0.05386   0.04874  -0.0533   1.0000   0.0433
 -11.250  -0.9405   0.05158   0.04628  -0.0471   1.0000   0.0433
 -11.000  -0.9610   0.04906   0.04353  -0.0413   1.0000   0.0433
 -10.750  -0.9777   0.04644   0.04062  -0.0358   1.0000   0.0434
 -10.500  -0.9898   0.04386   0.03769  -0.0306   1.0000   0.0435
 -10.250  -0.9972   0.04133   0.03479  -0.0259   1.0000   0.0439
 -10.000  -0.9936   0.03856   0.03187  -0.0232   1.0000   0.0445
  -9.750  -0.9844   0.03703   0.03027  -0.0208   1.0000   0.0453
  -9.500  -0.9723   0.03601   0.02921  -0.0187   1.0000   0.0465
  -9.250  -0.9623   0.03469   0.02772  -0.0161   1.0000   0.0479
  -9.000  -0.9529   0.03308   0.02579  -0.0134   1.0000   0.0494
  -8.750  -0.9425   0.03168   0.02397  -0.0106   1.0000   0.0507
  -8.500  -0.9261   0.02966   0.02188  -0.0092   1.0000   0.0522
  -8.250  -0.9090   0.02871   0.02088  -0.0077   1.0000   0.0539
  -8.000  -0.8917   0.02785   0.01992  -0.0061   1.0000   0.0560
  -7.750  -0.8744   0.02706   0.01887  -0.0044   1.0000   0.0585
  -7.500  -0.8552   0.02569   0.01746  -0.0032   1.0000   0.0609
  -7.250  -0.8361   0.02500   0.01676  -0.0020   1.0000   0.0634
  -7.000  -0.8168   0.02437   0.01601  -0.0006   1.0000   0.0665
  -6.750  -0.7969   0.02344   0.01497   0.0006   1.0000   0.0696
  -6.500  -0.7771   0.02275   0.01434   0.0017   1.0000   0.0728
  -6.250  -0.7570   0.02227   0.01378   0.0029   1.0000   0.0767
  -6.000  -0.7366   0.02151   0.01296   0.0041   1.0000   0.0806
  -5.750  -0.7166   0.02094   0.01246   0.0052   1.0000   0.0848
  -5.500  -0.6874   0.02064   0.01205   0.0046   0.9983   0.0904
  -5.250  -0.6549   0.01994   0.01147   0.0031   0.9957   0.0973
  -5.000  -0.6212   0.01956   0.01105   0.0016   0.9930   0.1057
  -4.750  -0.5904   0.01915   0.01069   0.0005   0.9895   0.1155
  -4.500  -0.5579   0.01871   0.01034  -0.0009   0.9863   0.1287
  -4.250  -0.5226   0.01841   0.01009  -0.0029   0.9837   0.1478
  -4.000  -0.4956   0.01783   0.00973  -0.0033   0.9794   0.1737
  -3.750  -0.4653   0.01725   0.00946  -0.0044   0.9756   0.2227
  -3.500  -0.4343   0.01637   0.00924  -0.0060   0.9728   0.3454
  -3.250  -0.4079   0.01546   0.00927  -0.0063   0.9695   0.5340
  -3.000  -0.3839   0.01517   0.00941  -0.0055   0.9642   0.6372
  -2.750  -0.3516   0.01524   0.00964  -0.0061   0.9604   0.7001
  -2.500  -0.3148   0.01544   0.00992  -0.0077   0.9576   0.7422
  -2.250  -0.2937   0.01543   0.00995  -0.0062   0.9507   0.7717
  -2.000  -0.2619   0.01555   0.01014  -0.0066   0.9464   0.7985
  -1.750  -0.2256   0.01575   0.01036  -0.0080   0.9433   0.8239
  -1.500  -0.2045   0.01583   0.01049  -0.0063   0.9363   0.8444
  -1.250  -0.1737   0.01599   0.01066  -0.0064   0.9314   0.8644
  -1.000  -0.1374   0.01620   0.01088  -0.0076   0.9283   0.8832
  -0.750  -0.1142   0.01639   0.01108  -0.0062   0.9214   0.9014
  -0.500  -0.0815   0.01667   0.01137  -0.0065   0.9165   0.9215
  -0.250  -0.0383   0.01709   0.01177  -0.0088   0.9139   0.9405
   0.000   0.0171   0.01740   0.01206  -0.0141   0.9126   0.9467
   0.250   0.0673   0.01754   0.01218  -0.0188   0.9105   0.9522
   0.500   0.1039   0.01765   0.01230  -0.0209   0.9028   0.9592
   0.750   0.1577   0.01767   0.01232  -0.0263   0.9000   0.9619
   1.000   0.2124   0.01759   0.01226  -0.0318   0.8979   0.9648
   1.250   0.2721   0.01728   0.01197  -0.0381   0.8959   0.9661
   1.500   0.3195   0.01662   0.01133  -0.0413   0.8849   0.9701
   1.750   0.3906   0.01541   0.01015  -0.0486   0.8803   0.9669
   2.000   0.4302   0.01495   0.00974  -0.0506   0.8697   0.9719
   2.250   0.4837   0.01416   0.00900  -0.0550   0.8638   0.9733
   2.500   0.5244   0.01368   0.00858  -0.0572   0.8507   0.9778
   2.750   0.5624   0.01319   0.00815  -0.0587   0.8361   0.9834
   3.000   0.6055   0.01264   0.00764  -0.0613   0.8170   0.9869
   3.250   0.6441   0.01222   0.00726  -0.0631   0.7889   0.9921
   3.500   0.6846   0.01179   0.00676  -0.0652   0.7451   0.9959
   3.750   0.7233   0.01166   0.00628  -0.0668   0.6705   0.9994
   4.000   0.7383   0.01204   0.00621  -0.0641   0.5793   1.0000
   4.250   0.7407   0.01277   0.00635  -0.0593   0.4681   1.0000
   4.500   0.7380   0.01370   0.00666  -0.0539   0.3566   1.0000
   4.750   0.7375   0.01457   0.00703  -0.0489   0.2733   1.0000
   5.000   0.7405   0.01529   0.00741  -0.0445   0.2199   1.0000
   5.250   0.7460   0.01591   0.00780  -0.0406   0.1861   1.0000
   5.500   0.7539   0.01644   0.00819  -0.0369   0.1623   1.0000
   5.750   0.7623   0.01697   0.00860  -0.0334   0.1451   1.0000
   6.000   0.7716   0.01749   0.00905  -0.0299   0.1318   1.0000
   6.250   0.7811   0.01808   0.00954  -0.0265   0.1212   1.0000
   6.500   0.7922   0.01861   0.01001  -0.0235   0.1122   1.0000
   6.750   0.8048   0.01917   0.01057  -0.0207   0.1044   1.0000
   7.000   0.8170   0.01986   0.01116  -0.0179   0.0976   1.0000
   7.250   0.8319   0.02041   0.01176  -0.0155   0.0918   1.0000
   7.500   0.8459   0.02101   0.01232  -0.0131   0.0866   1.0000
   7.750   0.8636   0.02184   0.01315  -0.0114   0.0816   1.0000
   8.000   0.8802   0.02243   0.01376  -0.0094   0.0772   1.0000
   8.250   0.9033   0.02359   0.01483  -0.0090   0.0728   1.0000
   8.500   0.9207   0.02419   0.01555  -0.0072   0.0692   1.0000
   8.750   0.9396   0.02492   0.01628  -0.0058   0.0659   1.0000
   9.000   0.9663   0.02631   0.01764  -0.0061   0.0625   1.0000
   9.250   0.9840   0.02707   0.01856  -0.0044   0.0597   1.0000
   9.500   1.0034   0.02797   0.01951  -0.0032   0.0573   1.0000
   9.750   1.0331   0.02976   0.02120  -0.0042   0.0547   1.0000
  10.000   1.0482   0.03083   0.02254  -0.0022   0.0530   1.0000
  10.250   1.0642   0.03195   0.02384  -0.0004   0.0510   1.0000
  10.500   1.0801   0.03300   0.02497   0.0012   0.0492   1.0000
  10.750   1.1001   0.03438   0.02635   0.0019   0.0478   1.0000
  11.000   1.1183   0.03690   0.02905   0.0027   0.0466   1.0000
  11.250   1.1233   0.03865   0.03116   0.0060   0.0458   1.0000
  11.500   1.1253   0.04064   0.03347   0.0095   0.0450   1.0000
  11.750   1.1250   0.04270   0.03581   0.0131   0.0442   1.0000
  12.000   1.1236   0.04472   0.03808   0.0166   0.0435   1.0000
  12.250   1.1228   0.04664   0.04018   0.0197   0.0427   1.0000
  12.500   1.1253   0.04837   0.04201   0.0221   0.0420   1.0000
  12.750   1.1307   0.05010   0.04381   0.0240   0.0414   1.0000
  13.000   1.1270   0.05261   0.04647   0.0265   0.0410   1.0000
  13.250   1.1181   0.05563   0.04968   0.0291   0.0407   1.0000
  13.500   1.1025   0.05909   0.05337   0.0317   0.0406   1.0000
  13.750   1.0809   0.06295   0.05749   0.0340   0.0407   1.0000
  14.000   1.0462   0.06801   0.06289   0.0355   0.0409   1.0000
<< Back to LOCKHEED C-141 BL0 AIRFOIL (c141a-il)

Polar data table (+)

Polar graphs


<< Back to LOCKHEED C-141 BL0 AIRFOIL (c141a-il)