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

NACA/LANGLEY SYMMETRICAL (n0011sc-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA/LANGLEY SYMMETRICAL (n0011sc-il)
Reynolds number: 500,000
Max Cl/Cd: 49.56 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n0011sc-il-500000.txt
Download as CSV file: xf-n0011sc-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA/LANGLEY SYMMETRICAL                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.7318   0.10342   0.10068  -0.0336   1.0000   0.0283
 -13.750  -0.8608   0.06982   0.06675  -0.0560   1.0000   0.0265
 -13.500  -0.9135   0.05984   0.05651  -0.0609   1.0000   0.0261
 -13.250  -0.9737   0.05178   0.04808  -0.0604   1.0000   0.0258
 -13.000  -1.0046   0.04786   0.04393  -0.0571   1.0000   0.0257
 -12.750  -1.0286   0.04496   0.04082  -0.0527   1.0000   0.0258
 -12.500  -1.0603   0.04164   0.03721  -0.0464   1.0000   0.0256
 -12.250  -1.0791   0.03956   0.03491  -0.0405   1.0000   0.0256
 -12.000  -1.0950   0.03782   0.03299  -0.0343   1.0000   0.0257
 -11.750  -1.1101   0.03635   0.03133  -0.0276   1.0000   0.0257
 -11.500  -1.1222   0.03504   0.02985  -0.0211   1.0000   0.0258
 -11.250  -1.1263   0.03359   0.02823  -0.0161   1.0000   0.0259
 -11.000  -1.1268   0.03219   0.02666  -0.0115   1.0000   0.0261
 -10.750  -1.1240   0.03100   0.02531  -0.0074   1.0000   0.0263
 -10.500  -1.1197   0.02974   0.02387  -0.0035   1.0000   0.0266
 -10.250  -1.1134   0.02855   0.02251   0.0001   1.0000   0.0269
 -10.000  -1.1051   0.02742   0.02122   0.0035   1.0000   0.0271
  -9.750  -1.0954   0.02644   0.02007   0.0067   1.0000   0.0274
  -9.500  -1.0840   0.02551   0.01899   0.0095   1.0000   0.0276
  -9.250  -1.0724   0.02489   0.01821   0.0126   1.0000   0.0280
  -9.000  -1.0585   0.02336   0.01659   0.0148   1.0000   0.0285
  -8.750  -1.0441   0.02253   0.01575   0.0171   1.0000   0.0290
  -8.500  -1.0294   0.02197   0.01516   0.0195   1.0000   0.0295
  -8.250  -1.0143   0.02139   0.01454   0.0218   1.0000   0.0300
  -8.000  -0.9988   0.02076   0.01384   0.0241   1.0000   0.0306
  -7.750  -0.9830   0.02020   0.01322   0.0263   1.0000   0.0312
  -7.500  -0.9620   0.01964   0.01258   0.0275   0.9995   0.0317
  -7.250  -0.9333   0.01919   0.01204   0.0271   0.9978   0.0325
  -7.000  -0.9069   0.01828   0.01112   0.0270   0.9960   0.0335
  -6.750  -0.8776   0.01786   0.01072   0.0264   0.9944   0.0346
  -6.500  -0.8514   0.01747   0.01031   0.0265   0.9923   0.0358
  -6.250  -0.8244   0.01712   0.00990   0.0265   0.9900   0.0372
  -6.000  -0.7977   0.01656   0.00935   0.0265   0.9878   0.0389
  -5.750  -0.7681   0.01626   0.00906   0.0259   0.9861   0.0408
  -5.500  -0.7369   0.01605   0.00882   0.0250   0.9848   0.0429
  -5.250  -0.7153   0.01553   0.00831   0.0262   0.9813   0.0453
  -5.000  -0.6888   0.01525   0.00804   0.0264   0.9786   0.0480
  -4.750  -0.6598   0.01494   0.00773   0.0260   0.9764   0.0516
  -4.500  -0.6284   0.01472   0.00755   0.0251   0.9748   0.0562
  -4.250  -0.5962   0.01446   0.00734   0.0240   0.9736   0.0624
  -4.000  -0.5766   0.01416   0.00704   0.0258   0.9689   0.0681
  -3.750  -0.5492   0.01389   0.00682   0.0258   0.9660   0.0777
  -3.500  -0.5191   0.01358   0.00663   0.0252   0.9639   0.0932
  -3.250  -0.4867   0.01332   0.00648   0.0241   0.9623   0.1143
  -3.000  -0.4536   0.01301   0.00637   0.0227   0.9611   0.1486
  -2.750  -0.4387   0.01264   0.00616   0.0254   0.9548   0.1830
  -2.500  -0.4113   0.01222   0.00601   0.0254   0.9519   0.2412
  -2.250  -0.3826   0.01168   0.00585   0.0249   0.9497   0.3270
  -2.000  -0.3573   0.01089   0.00569   0.0252   0.9478   0.4703
  -1.750  -0.3554   0.01019   0.00549   0.0309   0.9394   0.5873
  -1.500  -0.3411   0.00936   0.00537   0.0342   0.9356   0.7456
  -1.250  -0.2764   0.00928   0.00581   0.0265   0.9379   0.8718
  -1.000  -0.2186   0.00953   0.00609   0.0202   0.9389   0.9003
  -0.750  -0.1676   0.00970   0.00627   0.0157   0.9377   0.9135
  -0.500  -0.1075   0.00959   0.00613   0.0096   0.9351   0.9205
  -0.250  -0.0402   0.00958   0.00610   0.0020   0.9338   0.9231
   0.000  -0.0134   0.00963   0.00615   0.0029   0.9261   0.9317
   0.250   0.0393   0.00956   0.00609  -0.0018   0.9231   0.9337
   0.500   0.1063   0.00960   0.00614  -0.0094   0.9207   0.9351
   0.750   0.1686   0.00970   0.00627  -0.0160   0.9144   0.9376
   1.000   0.2204   0.00952   0.00609  -0.0207   0.9014   0.9386
   1.250   0.2762   0.00928   0.00581  -0.0265   0.8719   0.9379
   1.500   0.3417   0.00933   0.00538  -0.0344   0.7539   0.9356
   1.750   0.3554   0.01019   0.00549  -0.0309   0.5877   0.9394
   2.000   0.3566   0.01092   0.00569  -0.0250   0.4633   0.9479
   2.250   0.3828   0.01168   0.00585  -0.0250   0.3278   0.9497
   2.500   0.4114   0.01221   0.00600  -0.0254   0.2432   0.9519
   2.750   0.4387   0.01264   0.00616  -0.0255   0.1831   0.9549
   3.000   0.4536   0.01300   0.00636  -0.0228   0.1494   0.9611
   3.250   0.4869   0.01332   0.00648  -0.0241   0.1150   0.9623
   3.500   0.5189   0.01358   0.00662  -0.0251   0.0922   0.9639
   3.750   0.5491   0.01389   0.00682  -0.0257   0.0774   0.9660
   4.000   0.5766   0.01416   0.00703  -0.0258   0.0679   0.9689
   4.250   0.5963   0.01446   0.00732  -0.0240   0.0618   0.9736
   4.500   0.6285   0.01470   0.00752  -0.0251   0.0560   0.9748
   4.750   0.6596   0.01497   0.00775  -0.0260   0.0512   0.9765
   5.000   0.6888   0.01525   0.00804  -0.0264   0.0480   0.9786
   5.250   0.7152   0.01553   0.00831  -0.0262   0.0451   0.9814
   5.500   0.7369   0.01604   0.00881  -0.0251   0.0430   0.9848
   5.750   0.7683   0.01626   0.00906  -0.0259   0.0408   0.9861
   6.000   0.7977   0.01657   0.00935  -0.0265   0.0389   0.9878
   6.250   0.8246   0.01712   0.00990  -0.0266   0.0371   0.9900
   6.500   0.8518   0.01742   0.01026  -0.0266   0.0356   0.9923
   6.750   0.8778   0.01784   0.01069  -0.0264   0.0344   0.9945
   7.000   0.9069   0.01830   0.01114  -0.0270   0.0333   0.9961
   7.250   0.9336   0.01913   0.01199  -0.0272   0.0323   0.9978
   7.500   0.9621   0.01966   0.01260  -0.0275   0.0317   0.9995
   7.750   0.9829   0.02018   0.01321  -0.0263   0.0310   1.0000
   8.000   0.9987   0.02078   0.01386  -0.0240   0.0304   1.0000
   8.250   1.0141   0.02135   0.01449  -0.0218   0.0299   1.0000
   8.500   1.0293   0.02199   0.01519  -0.0194   0.0295   1.0000
   8.750   1.0440   0.02260   0.01582  -0.0171   0.0289   1.0000
   9.000   1.0585   0.02342   0.01667  -0.0148   0.0286   1.0000
   9.250   1.0724   0.02491   0.01824  -0.0126   0.0280   1.0000
   9.500   1.0843   0.02554   0.01901  -0.0096   0.0277   1.0000
   9.750   1.0954   0.02647   0.02010  -0.0067   0.0275   1.0000
  10.000   1.1051   0.02748   0.02128  -0.0035   0.0272   1.0000
  10.250   1.1133   0.02856   0.02253  -0.0001   0.0269   1.0000
  10.500   1.1197   0.02981   0.02395   0.0035   0.0267   1.0000
  10.750   1.1237   0.03107   0.02538   0.0075   0.0264   1.0000
  11.000   1.1254   0.03245   0.02694   0.0117   0.0262   1.0000
  11.250   1.1239   0.03395   0.02864   0.0164   0.0261   1.0000
  11.500   1.1210   0.03518   0.03002   0.0213   0.0258   1.0000
  11.750   1.1093   0.03644   0.03143   0.0277   0.0257   1.0000
  12.000   1.0927   0.03808   0.03327   0.0345   0.0258   1.0000
  12.250   1.0739   0.04002   0.03543   0.0411   0.0258   1.0000
  12.500   1.0627   0.04147   0.03701   0.0461   0.0255   1.0000
  12.750   1.0337   0.04456   0.04038   0.0522   0.0257   1.0000
  13.000   1.0142   0.04706   0.04306   0.0564   0.0256   1.0000
  13.250   0.9576   0.05345   0.04985   0.0606   0.0260   1.0000
  13.500   0.9193   0.05920   0.05584   0.0611   0.0262   1.0000
  13.750   0.8565   0.07069   0.06765   0.0552   0.0265   1.0000
  14.000   0.7253   0.10506   0.10231   0.0327   0.0282   1.0000
<< Back to NACA/LANGLEY SYMMETRICAL (n0011sc-il)

Polar data table (+)

Polar graphs


<< Back to NACA/LANGLEY SYMMETRICAL (n0011sc-il)