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

NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.62 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ls417-il-1000000.txt
Download as CSV file: xf-ls417-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0417 (GA(W)-1) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.750  -0.8636   0.10904   0.10626  -0.0535   1.0000   0.0155
 -18.500  -0.8958   0.09877   0.09580  -0.0596   1.0000   0.0154
 -18.250  -0.9195   0.09040   0.08726  -0.0647   1.0000   0.0154
 -18.000  -0.9380   0.08321   0.07992  -0.0690   1.0000   0.0155
 -17.750  -0.9517   0.07700   0.07358  -0.0728   1.0000   0.0155
 -17.500  -0.9625   0.07147   0.06791  -0.0760   1.0000   0.0155
 -17.250  -0.9709   0.06650   0.06281  -0.0789   1.0000   0.0156
 -17.000  -0.9767   0.06211   0.05830  -0.0814   1.0000   0.0156
 -16.750  -0.9808   0.05816   0.05423  -0.0834   1.0000   0.0157
 -16.500  -0.9832   0.05463   0.05059  -0.0851   1.0000   0.0157
 -16.250  -0.9842   0.05145   0.04730  -0.0865   1.0000   0.0158
 -16.000  -0.9842   0.04856   0.04432  -0.0875   1.0000   0.0158
 -15.750  -0.9887   0.04535   0.04097  -0.0880   1.0000   0.0159
 -15.500  -0.9910   0.04246   0.03796  -0.0880   1.0000   0.0160
 -15.250  -0.9895   0.04005   0.03547  -0.0880   1.0000   0.0161
 -15.000  -0.9850   0.03798   0.03333  -0.0880   1.0000   0.0162
 -14.750  -0.9792   0.03611   0.03142  -0.0879   1.0000   0.0163
 -14.500  -0.9690   0.03441   0.02966  -0.0883   0.9951   0.0164
 -14.250  -0.9523   0.03270   0.02789  -0.0898   0.9818   0.0165
 -14.000  -0.9383   0.03123   0.02635  -0.0903   0.9655   0.0167
 -13.750  -0.9288   0.02994   0.02498  -0.0896   0.9480   0.0168
 -13.500  -0.9189   0.02876   0.02370  -0.0887   0.9337   0.0169
 -13.250  -0.9072   0.02762   0.02247  -0.0880   0.9219   0.0170
 -13.000  -0.8944   0.02654   0.02130  -0.0874   0.9122   0.0172
 -12.750  -0.8806   0.02552   0.02019  -0.0869   0.9031   0.0173
 -12.500  -0.8660   0.02453   0.01912  -0.0864   0.8955   0.0175
 -12.250  -0.8503   0.02358   0.01810  -0.0860   0.8885   0.0177
 -12.000  -0.8346   0.02268   0.01711  -0.0855   0.8814   0.0178
 -11.750  -0.8178   0.02183   0.01619  -0.0850   0.8752   0.0180
 -11.500  -0.8005   0.02101   0.01532  -0.0846   0.8692   0.0182
 -11.250  -0.7843   0.02028   0.01451  -0.0839   0.8632   0.0184
 -11.000  -0.7665   0.01964   0.01379  -0.0834   0.8574   0.0186
 -10.750  -0.7445   0.01900   0.01311  -0.0836   0.8535   0.0187
 -10.500  -0.7247   0.01804   0.01210  -0.0838   0.8490   0.0190
 -10.250  -0.7037   0.01711   0.01112  -0.0841   0.8444   0.0194
 -10.000  -0.6798   0.01650   0.01046  -0.0845   0.8400   0.0197
  -9.750  -0.6545   0.01602   0.00995  -0.0849   0.8362   0.0201
  -9.500  -0.6284   0.01556   0.00947  -0.0853   0.8332   0.0206
  -9.250  -0.6020   0.01511   0.00900  -0.0857   0.8298   0.0210
  -9.000  -0.5752   0.01469   0.00854  -0.0861   0.8264   0.0214
  -8.750  -0.5480   0.01431   0.00811  -0.0865   0.8230   0.0218
  -8.500  -0.5207   0.01391   0.00766  -0.0870   0.8192   0.0222
  -8.250  -0.4935   0.01334   0.00707  -0.0877   0.8160   0.0229
  -8.000  -0.4651   0.01295   0.00668  -0.0883   0.8134   0.0236
  -7.750  -0.4362   0.01261   0.00633  -0.0889   0.8106   0.0244
  -7.500  -0.4071   0.01231   0.00601  -0.0896   0.8078   0.0252
  -7.250  -0.3779   0.01194   0.00562  -0.0903   0.8051   0.0263
  -7.000  -0.3484   0.01162   0.00529  -0.0910   0.8023   0.0277
  -6.750  -0.3185   0.01139   0.00502  -0.0917   0.7991   0.0293
  -6.500  -0.2884   0.01107   0.00473  -0.0926   0.7966   0.0325
  -6.250  -0.2580   0.01074   0.00447  -0.0935   0.7946   0.0401
  -6.000  -0.2273   0.01044   0.00425  -0.0944   0.7924   0.0539
  -5.750  -0.1964   0.01016   0.00402  -0.0954   0.7901   0.0650
  -5.500  -0.1653   0.00985   0.00381  -0.0964   0.7877   0.0814
  -5.250  -0.1339   0.00952   0.00360  -0.0976   0.7852   0.1097
  -5.000  -0.1023   0.00924   0.00342  -0.0987   0.7827   0.1338
  -4.750  -0.0700   0.00889   0.00323  -0.1002   0.7800   0.1749
  -4.500  -0.0366   0.00845   0.00304  -0.1020   0.7774   0.2379
  -4.250  -0.0025   0.00797   0.00285  -0.1040   0.7759   0.3092
  -4.000   0.0316   0.00759   0.00269  -0.1058   0.7741   0.3698
  -3.750   0.0665   0.00716   0.00252  -0.1078   0.7719   0.4425
  -3.500   0.1025   0.00669   0.00240  -0.1101   0.7697   0.5372
  -3.250   0.1353   0.00658   0.00243  -0.1112   0.7674   0.5900
  -3.000   0.1668   0.00659   0.00246  -0.1120   0.7651   0.6097
  -2.750   0.1980   0.00664   0.00248  -0.1126   0.7628   0.6218
  -2.500   0.2291   0.00669   0.00251  -0.1133   0.7600   0.6294
  -2.250   0.2601   0.00676   0.00257  -0.1139   0.7574   0.6356
  -2.000   0.2914   0.00679   0.00258  -0.1146   0.7557   0.6420
  -1.750   0.3222   0.00678   0.00260  -0.1152   0.7530   0.6485
  -1.500   0.3529   0.00680   0.00262  -0.1157   0.7493   0.6537
  -1.250   0.3836   0.00683   0.00262  -0.1162   0.7447   0.6597
  -1.000   0.4139   0.00692   0.00265  -0.1166   0.7384   0.6661
  -0.750   0.4441   0.00688   0.00266  -0.1169   0.7325   0.6711
  -0.500   0.4745   0.00688   0.00264  -0.1174   0.7263   0.6740
  -0.250   0.5049   0.00692   0.00264  -0.1179   0.7215   0.6766
   0.000   0.5356   0.00695   0.00266  -0.1184   0.7171   0.6789
   0.250   0.5664   0.00695   0.00267  -0.1190   0.7123   0.6808
   0.500   0.5969   0.00696   0.00267  -0.1196   0.7076   0.6839
   0.750   0.6267   0.00700   0.00269  -0.1199   0.7014   0.6881
   1.000   0.6568   0.00702   0.00274  -0.1203   0.6941   0.6914
   1.250   0.6866   0.00706   0.00276  -0.1206   0.6852   0.6940
   1.500   0.7167   0.00710   0.00280  -0.1211   0.6771   0.6964
   1.750   0.7467   0.00715   0.00283  -0.1215   0.6668   0.6985
   2.000   0.7766   0.00722   0.00286  -0.1219   0.6553   0.7002
   2.250   0.8058   0.00732   0.00290  -0.1222   0.6392   0.7014
   2.500   0.8345   0.00741   0.00293  -0.1224   0.6166   0.7035
   2.750   0.8603   0.00770   0.00304  -0.1221   0.5718   0.7055
   3.000   0.8828   0.00829   0.00332  -0.1213   0.5057   0.7073
   3.250   0.9047   0.00894   0.00367  -0.1204   0.4440   0.7090
   3.500   0.9274   0.00950   0.00399  -0.1196   0.3932   0.7105
   3.750   0.9496   0.01006   0.00431  -0.1188   0.3460   0.7122
   4.000   0.9723   0.01057   0.00463  -0.1180   0.3062   0.7138
   4.250   0.9949   0.01106   0.00494  -0.1173   0.2716   0.7155
   4.500   1.0177   0.01151   0.00523  -0.1165   0.2417   0.7171
   4.750   1.0402   0.01196   0.00555  -0.1157   0.2173   0.7188
   5.000   1.0634   0.01235   0.00583  -0.1150   0.1976   0.7202
   5.250   1.0859   0.01272   0.00612  -0.1143   0.1790   0.7223
   5.500   1.1080   0.01310   0.00643  -0.1134   0.1638   0.7242
   5.750   1.1298   0.01348   0.00675  -0.1124   0.1520   0.7260
   6.000   1.1514   0.01384   0.00707  -0.1114   0.1426   0.7279
   6.250   1.1728   0.01418   0.00739  -0.1104   0.1343   0.7298
   6.500   1.1923   0.01460   0.00776  -0.1090   0.1256   0.7318
   6.750   1.2103   0.01494   0.00808  -0.1073   0.1193   0.7339
   7.000   1.2259   0.01536   0.00848  -0.1052   0.1129   0.7359
   7.250   1.2446   0.01581   0.00890  -0.1038   0.1069   0.7377
   7.500   1.2635   0.01628   0.00935  -0.1025   0.1013   0.7397
   7.750   1.2825   0.01674   0.00981  -0.1012   0.0969   0.7422
   8.000   1.3004   0.01728   0.01035  -0.0999   0.0927   0.7445
   8.250   1.3203   0.01773   0.01082  -0.0988   0.0901   0.7469
   8.500   1.3386   0.01828   0.01137  -0.0976   0.0873   0.7495
   8.750   1.3553   0.01893   0.01202  -0.0961   0.0842   0.7521
   9.000   1.3746   0.01944   0.01256  -0.0951   0.0825   0.7546
   9.250   1.3935   0.01999   0.01313  -0.0941   0.0805   0.7569
   9.500   1.4111   0.02062   0.01378  -0.0929   0.0785   0.7600
   9.750   1.4270   0.02136   0.01454  -0.0915   0.0763   0.7628
  10.000   1.4444   0.02202   0.01524  -0.0904   0.0747   0.7656
  10.250   1.4628   0.02262   0.01589  -0.0894   0.0733   0.7685
  10.500   1.4801   0.02331   0.01660  -0.0883   0.0718   0.7713
  10.750   1.4961   0.02410   0.01740  -0.0872   0.0701   0.7741
  11.000   1.5100   0.02502   0.01834  -0.0857   0.0682   0.7774
  11.250   1.5270   0.02574   0.01912  -0.0847   0.0670   0.7806
  11.500   1.5439   0.02647   0.01991  -0.0837   0.0658   0.7840
  11.750   1.5599   0.02728   0.02075  -0.0827   0.0643   0.7875
  12.000   1.5742   0.02823   0.02170  -0.0815   0.0629   0.7907
  12.250   1.5863   0.02932   0.02282  -0.0801   0.0612   0.7944
  12.500   1.6016   0.03018   0.02375  -0.0790   0.0601   0.7980
  12.750   1.6169   0.03106   0.02469  -0.0780   0.0589   0.8017
  13.000   1.6312   0.03203   0.02569  -0.0770   0.0573   0.8053
  13.250   1.6431   0.03319   0.02686  -0.0758   0.0558   0.8087
  13.500   1.6544   0.03439   0.02811  -0.0745   0.0543   0.8125
  13.750   1.6689   0.03535   0.02914  -0.0736   0.0530   0.8163
  14.000   1.6811   0.03653   0.03037  -0.0725   0.0514   0.8202
  14.250   1.6919   0.03784   0.03169  -0.0714   0.0499   0.8238
  14.500   1.7018   0.03926   0.03316  -0.0702   0.0484   0.8278
  14.750   1.7140   0.04049   0.03446  -0.0693   0.0470   0.8321
  15.000   1.7244   0.04187   0.03589  -0.0683   0.0455   0.8366
  15.250   1.7316   0.04359   0.03764  -0.0671   0.0440   0.8409
  15.500   1.7414   0.04509   0.03921  -0.0662   0.0428   0.8455
  15.750   1.7500   0.04672   0.04091  -0.0653   0.0415   0.8504
  16.000   1.7574   0.04851   0.04274  -0.0644   0.0402   0.8554
  16.250   1.7614   0.05066   0.04493  -0.0634   0.0390   0.8601
  16.500   1.7685   0.05249   0.04686  -0.0625   0.0381   0.8655
  16.750   1.7744   0.05452   0.04896  -0.0618   0.0372   0.8713
  17.000   1.7791   0.05669   0.05120  -0.0610   0.0362   0.8770
  17.250   1.7810   0.05919   0.05377  -0.0603   0.0354   0.8836
  17.750   1.7833   0.06450   0.05925  -0.0591   0.0339   0.8989
  18.000   1.7852   0.06707   0.06194  -0.0587   0.0334   0.9091
  18.250   1.7855   0.06974   0.06473  -0.0581   0.0327   0.9270
  18.500   1.7807   0.07266   0.06777  -0.0572   0.0322   1.0000
  18.750   1.7779   0.07614   0.07132  -0.0573   0.0317   1.0000
  19.000   1.7724   0.08001   0.07526  -0.0576   0.0312   1.0000
  19.250   1.7632   0.08443   0.07977  -0.0581   0.0307   1.0000
<< Back to NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il)

Polar data table (+)

Polar graphs


<< Back to NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il)