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AUGUST 160 (august160-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: AUGUST 160 (august160-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.17 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-august160-il-1000000-n5.txt
Download as CSV file: xf-august160-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AUGUST 160                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4918   0.03717   0.03306  -0.0828   0.4648   0.0081
 -10.500  -0.5099   0.03465   0.03036  -0.0784   0.4617   0.0082
 -10.250  -0.5239   0.03193   0.02740  -0.0743   0.4573   0.0081
 -10.000  -0.5288   0.02940   0.02458  -0.0708   0.4521   0.0082
  -9.750  -0.5241   0.02759   0.02255  -0.0680   0.4467   0.0082
  -9.500  -0.5162   0.02591   0.02063  -0.0655   0.4394   0.0082
  -9.250  -0.5035   0.02466   0.01918  -0.0634   0.4330   0.0083
  -9.000  -0.4875   0.02367   0.01802  -0.0617   0.4276   0.0083
  -8.750  -0.4740   0.02225   0.01639  -0.0596   0.4220   0.0083
  -8.500  -0.4616   0.02059   0.01448  -0.0573   0.4158   0.0085
  -8.250  -0.4433   0.01959   0.01332  -0.0557   0.4110   0.0085
  -8.000  -0.4231   0.01877   0.01237  -0.0543   0.4062   0.0086
  -7.750  -0.4013   0.01818   0.01168  -0.0532   0.4010   0.0087
  -7.500  -0.3800   0.01744   0.01080  -0.0519   0.3954   0.0087
  -7.250  -0.3567   0.01697   0.01026  -0.0510   0.3914   0.0088
  -7.000  -0.3336   0.01642   0.00960  -0.0499   0.3871   0.0089
  -6.750  -0.3095   0.01604   0.00915  -0.0491   0.3825   0.0090
  -6.500  -0.2850   0.01572   0.00875  -0.0483   0.3778   0.0092
  -6.250  -0.2607   0.01529   0.00825  -0.0474   0.3745   0.0093
  -6.000  -0.2361   0.01486   0.00774  -0.0466   0.3711   0.0095
  -5.750  -0.2115   0.01444   0.00725  -0.0458   0.3674   0.0096
  -5.500  -0.1869   0.01404   0.00677  -0.0449   0.3633   0.0097
  -5.250  -0.1622   0.01367   0.00632  -0.0441   0.3594   0.0098
  -5.000  -0.1371   0.01331   0.00591  -0.0433   0.3566   0.0099
  -4.750  -0.1117   0.01299   0.00553  -0.0426   0.3537   0.0102
  -4.500  -0.0863   0.01270   0.00519  -0.0419   0.3506   0.0103
  -4.250  -0.0607   0.01245   0.00489  -0.0412   0.3473   0.0105
  -4.000  -0.0351   0.01223   0.00462  -0.0405   0.3438   0.0106
  -3.750  -0.0092   0.01204   0.00438  -0.0399   0.3406   0.0107
  -3.500   0.0170   0.01186   0.00417  -0.0393   0.3384   0.0109
  -3.250   0.0422   0.01156   0.00384  -0.0386   0.3357   0.0112
  -3.000   0.0680   0.01134   0.00360  -0.0379   0.3330   0.0114
  -2.750   0.0941   0.01120   0.00343  -0.0374   0.3305   0.0117
  -2.500   0.1204   0.01107   0.00327  -0.0368   0.3279   0.0119
  -2.250   0.1467   0.01096   0.00313  -0.0363   0.3252   0.0122
  -2.000   0.1733   0.01085   0.00301  -0.0358   0.3236   0.0124
  -1.750   0.2000   0.01075   0.00290  -0.0354   0.3222   0.0127
  -1.500   0.2268   0.01066   0.00279  -0.0350   0.3207   0.0130
  -1.250   0.2536   0.01059   0.00271  -0.0346   0.3189   0.0134
  -1.000   0.2803   0.01052   0.00262  -0.0341   0.3171   0.0141
  -0.750   0.3070   0.01046   0.00255  -0.0337   0.3152   0.0147
  -0.500   0.3337   0.01042   0.00250  -0.0333   0.3134   0.0156
  -0.250   0.3604   0.01040   0.00246  -0.0329   0.3114   0.0172
   0.000   0.3862   0.01030   0.00243  -0.0323   0.3094   0.0384
   0.250   0.4115   0.01016   0.00241  -0.0317   0.3078   0.0805
   0.500   0.4381   0.01008   0.00240  -0.0314   0.3070   0.1093
   0.750   0.4643   0.00999   0.00241  -0.0309   0.3059   0.1466
   1.000   0.4896   0.00985   0.00242  -0.0304   0.3049   0.2014
   1.250   0.5099   0.00936   0.00244  -0.0290   0.3036   0.3790
   1.500   0.5274   0.00883   0.00246  -0.0270   0.3024   0.5685
   1.750   0.5312   0.00801   0.00253  -0.0218   0.3013   0.8368
   2.000   0.5571   0.00800   0.00266  -0.0210   0.3000   0.9030
   2.250   0.5852   0.00808   0.00274  -0.0209   0.2984   0.9201
   2.500   0.6144   0.00818   0.00283  -0.0211   0.2969   0.9333
   2.750   0.6442   0.00830   0.00293  -0.0214   0.2953   0.9452
   3.000   0.6715   0.00841   0.00302  -0.0212   0.2937   0.9537
   3.250   0.7047   0.00855   0.00314  -0.0223   0.2921   0.9595
   3.500   0.7320   0.00863   0.00321  -0.0221   0.2915   0.9654
   3.750   0.7678   0.00874   0.00331  -0.0238   0.2904   0.9682
   4.000   0.8011   0.00884   0.00340  -0.0250   0.2889   0.9715
   4.250   0.8311   0.00894   0.00349  -0.0255   0.2877   0.9746
   4.500   0.8633   0.00905   0.00358  -0.0265   0.2852   0.9771
   4.750   0.8977   0.00918   0.00368  -0.0280   0.2833   0.9781
   5.000   0.9293   0.00932   0.00379  -0.0289   0.2805   0.9789
   5.250   0.9609   0.00948   0.00392  -0.0299   0.2778   0.9800
   5.500   0.9921   0.00961   0.00404  -0.0308   0.2767   0.9811
   5.750   1.0244   0.00973   0.00417  -0.0318   0.2757   0.9830
   6.000   1.0552   0.00985   0.00429  -0.0326   0.2747   0.9852
   6.250   1.0866   0.00998   0.00443  -0.0335   0.2738   0.9865
   6.500   1.1196   0.01012   0.00458  -0.0348   0.2726   0.9875
   6.750   1.1533   0.01027   0.00473  -0.0363   0.2717   0.9889
   7.000   1.1839   0.01041   0.00488  -0.0371   0.2707   0.9900
   7.250   1.2136   0.01056   0.00504  -0.0378   0.2696   0.9912
   7.500   1.2428   0.01071   0.00520  -0.0384   0.2687   0.9925
   7.750   1.2717   0.01087   0.00538  -0.0389   0.2677   0.9938
   8.000   1.3000   0.01104   0.00556  -0.0394   0.2667   0.9959
   8.250   1.3291   0.01124   0.00576  -0.0400   0.2650   0.9979
   8.500   1.3587   0.01145   0.00597  -0.0408   0.2635   0.9991
   8.750   1.3885   0.01162   0.00617  -0.0416   0.2619   1.0000
   9.000   1.4083   0.01174   0.00633  -0.0403   0.2605   1.0000
   9.250   1.4275   0.01188   0.00650  -0.0388   0.2591   1.0000
   9.500   1.4469   0.01204   0.00669  -0.0375   0.2584   1.0000
   9.750   1.4672   0.01221   0.00689  -0.0364   0.2568   1.0000
  10.000   1.4880   0.01239   0.00710  -0.0354   0.2555   1.0000
  10.250   1.5088   0.01260   0.00732  -0.0344   0.2533   1.0000
  10.500   1.5292   0.01284   0.00757  -0.0334   0.2509   1.0000
  10.750   1.5490   0.01312   0.00786  -0.0324   0.2485   1.0000
  11.000   1.5712   0.01329   0.00809  -0.0317   0.2469   1.0000
  11.250   1.5928   0.01350   0.00833  -0.0310   0.2448   1.0000
  11.500   1.6137   0.01373   0.00860  -0.0302   0.2412   1.0000
  11.750   1.6327   0.01405   0.00893  -0.0291   0.2368   1.0000
  12.000   1.6498   0.01438   0.00927  -0.0277   0.2324   1.0000
  12.250   1.6656   0.01472   0.00962  -0.0262   0.2255   1.0000
  12.500   1.6780   0.01523   0.01012  -0.0242   0.2174   1.0000
  12.750   1.6886   0.01587   0.01073  -0.0222   0.2095   1.0000
  13.000   1.6922   0.01690   0.01172  -0.0196   0.1969   1.0000
  13.250   1.6964   0.01802   0.01283  -0.0175   0.1854   1.0000
  13.500   1.6870   0.02017   0.01493  -0.0149   0.1680   1.0000
  13.750   1.6764   0.02292   0.01768  -0.0135   0.1565   1.0000
  14.000   1.6663   0.02620   0.02100  -0.0133   0.1486   1.0000
  14.250   1.6600   0.02944   0.02431  -0.0136   0.1423   1.0000
  14.750   1.6210   0.03901   0.03403  -0.0147   0.1282   1.0000
  15.000   1.5904   0.04504   0.04016  -0.0154   0.1228   1.0000
  15.250   1.5501   0.05218   0.04740  -0.0162   0.1180   1.0000
  15.500   1.5237   0.05789   0.05321  -0.0169   0.1159   1.0000
  15.750   1.4852   0.06533   0.06073  -0.0182   0.1116   1.0000
  16.000   1.4657   0.07067   0.06617  -0.0192   0.1099   1.0000
  16.250   1.4474   0.07592   0.07150  -0.0203   0.1077   1.0000
  16.500   1.4255   0.08172   0.07737  -0.0216   0.1048   1.0000
  16.750   1.4019   0.08789   0.08360  -0.0230   0.1010   1.0000
  17.000   1.3885   0.09277   0.08855  -0.0242   0.0970   1.0000
  17.250   1.3677   0.09870   0.09450  -0.0258   0.0892   1.0000
  17.500   1.3397   0.10576   0.10153  -0.0277   0.0790   1.0000
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