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

US1000ROOT (us1000root-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: US1000ROOT (us1000root-il)
Reynolds number: 100,000
Max Cl/Cd: 38.34 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-us1000root-il-100000.txt
Download as CSV file: xf-us1000root-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: US1000ROOT                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.7425   0.09877   0.09178  -0.0219   1.0000   0.0398
 -14.500  -0.7455   0.09485   0.08780  -0.0231   1.0000   0.0402
 -14.250  -0.7566   0.08973   0.08259  -0.0248   1.0000   0.0422
 -14.000  -0.7631   0.08534   0.07811  -0.0262   1.0000   0.0428
 -13.750  -0.7715   0.08072   0.07339  -0.0277   1.0000   0.0432
 -13.500  -0.7857   0.07538   0.06795  -0.0295   1.0000   0.0444
 -13.250  -0.8105   0.06871   0.06121  -0.0317   1.0000   0.0471
 -13.000  -0.8363   0.06218   0.05463  -0.0338   1.0000   0.0502
 -12.750  -0.8296   0.05996   0.05222  -0.0343   1.0000   0.0473
 -12.500  -0.8682   0.05230   0.04455  -0.0364   1.0000   0.0534
 -12.250  -0.8803   0.04816   0.04033  -0.0372   1.0000   0.0549
 -12.000  -0.9098   0.04263   0.03488  -0.0378   1.0000   0.0657
 -11.500  -0.9665   0.03394   0.02664  -0.0353   1.0000   0.1344
 -11.250  -0.9894   0.03117   0.02417  -0.0321   1.0000   0.1748
 -11.000  -1.0072   0.02959   0.02262  -0.0279   1.0000   0.2105
 -10.750  -1.0251   0.02902   0.02208  -0.0219   1.0000   0.2313
 -10.500  -1.0439   0.02894   0.02195  -0.0146   1.0000   0.2466
 -10.250  -1.0513   0.02903   0.02203  -0.0090   1.0000   0.2601
 -10.000  -1.0546   0.02957   0.02260  -0.0037   1.0000   0.2746
  -9.750  -1.0506   0.03060   0.02373   0.0007   1.0000   0.2899
  -9.500  -1.0372   0.03193   0.02519   0.0038   1.0000   0.3050
  -9.250  -1.0396   0.03124   0.02430   0.0084   1.0000   0.3122
  -9.000  -1.0144   0.03167   0.02482   0.0092   1.0000   0.3202
  -8.750  -1.0243   0.03076   0.02367   0.0149   1.0000   0.3261
  -8.500  -0.9978   0.03124   0.02433   0.0156   1.0000   0.3338
  -8.250  -1.0083   0.03046   0.02330   0.0213   1.0000   0.3398
  -8.000  -0.9873   0.03052   0.02349   0.0225   1.0000   0.3460
  -7.750  -0.9844   0.03000   0.02284   0.0262   1.0000   0.3519
  -7.500  -0.9807   0.02932   0.02201   0.0297   1.0000   0.3570
  -7.250  -0.9654   0.02904   0.02175   0.0316   1.0000   0.3618
  -7.000  -0.9620   0.02843   0.02095   0.0350   1.0000   0.3676
  -6.750  -0.9513   0.02794   0.02039   0.0373   1.0000   0.3725
  -6.500  -0.9375   0.02770   0.02013   0.0392   1.0000   0.3777
  -6.250  -0.9336   0.02713   0.01929   0.0425   1.0000   0.3838
  -6.000  -0.8835   0.02699   0.01921   0.0377   0.9913   0.3911
  -5.750  -0.8431   0.02645   0.01841   0.0342   0.9805   0.3998
  -5.500  -0.7935   0.02617   0.01818   0.0296   0.9712   0.4071
  -5.250  -0.7547   0.02559   0.01739   0.0268   0.9597   0.4153
  -5.000  -0.7103   0.02523   0.01705   0.0233   0.9491   0.4227
  -4.750  -0.6681   0.02470   0.01641   0.0201   0.9385   0.4312
  -4.500  -0.6175   0.02422   0.01588   0.0155   0.9297   0.4401
  -4.250  -0.5751   0.02375   0.01540   0.0126   0.9182   0.4486
  -4.000  -0.5323   0.02323   0.01475   0.0096   0.9078   0.4590
  -3.750  -0.4718   0.02263   0.01421   0.0036   0.9008   0.4693
  -3.500  -0.4252   0.02216   0.01375   0.0001   0.8893   0.4794
  -3.250  -0.3805   0.02170   0.01327  -0.0030   0.8772   0.4910
  -3.000  -0.3397   0.02129   0.01280  -0.0052   0.8639   0.5032
  -2.750  -0.2992   0.02093   0.01250  -0.0073   0.8495   0.5143
  -2.500  -0.2646   0.02064   0.01225  -0.0081   0.8337   0.5258
  -2.250  -0.2341   0.02037   0.01198  -0.0081   0.8173   0.5378
  -2.000  -0.2059   0.02012   0.01173  -0.0077   0.8009   0.5506
  -1.750  -0.1786   0.01986   0.01145  -0.0071   0.7845   0.5638
  -1.500  -0.1521   0.01961   0.01119  -0.0063   0.7684   0.5774
  -1.250  -0.1289   0.01942   0.01101  -0.0049   0.7509   0.5915
  -1.000  -0.1054   0.01925   0.01085  -0.0035   0.7334   0.6059
  -0.750  -0.0802   0.01908   0.01070  -0.0024   0.7164   0.6207
  -0.500  -0.0542   0.01896   0.01060  -0.0015   0.6999   0.6359
  -0.250  -0.0277   0.01888   0.01053  -0.0006   0.6835   0.6516
   0.000  -0.0010   0.01885   0.01051   0.0002   0.6674   0.6674
   0.250   0.0257   0.01887   0.01053   0.0010   0.6515   0.6835
   0.500   0.0522   0.01896   0.01060   0.0019   0.6360   0.6999
   0.750   0.0781   0.01908   0.01071   0.0029   0.6209   0.7164
   1.000   0.1033   0.01924   0.01086   0.0039   0.6060   0.7334
   1.250   0.1269   0.01941   0.01101   0.0053   0.5916   0.7509
   1.500   0.1500   0.01960   0.01119   0.0067   0.5776   0.7684
   1.750   0.1767   0.01985   0.01146   0.0075   0.5639   0.7846
   2.000   0.2039   0.02011   0.01173   0.0081   0.5508   0.8009
   2.250   0.2323   0.02036   0.01198   0.0085   0.5380   0.8174
   2.500   0.2628   0.02063   0.01224   0.0085   0.5258   0.8338
   2.750   0.2976   0.02092   0.01250   0.0076   0.5144   0.8498
   3.000   0.3378   0.02127   0.01281   0.0057   0.5033   0.8641
   3.250   0.3788   0.02168   0.01327   0.0034   0.4911   0.8773
   3.500   0.4238   0.02215   0.01376   0.0003   0.4795   0.8894
   3.750   0.4706   0.02261   0.01421  -0.0033   0.4694   0.9009
   4.000   0.5306   0.02320   0.01475  -0.0092   0.4590   0.9080
   4.250   0.5742   0.02374   0.01541  -0.0124   0.4486   0.9184
   4.500   0.6163   0.02419   0.01589  -0.0152   0.4401   0.9298
   4.750   0.6664   0.02468   0.01643  -0.0197   0.4313   0.9387
   5.000   0.7090   0.02521   0.01707  -0.0230   0.4228   0.9492
   5.250   0.7539   0.02557   0.01741  -0.0265   0.4152   0.9600
   5.500   0.7928   0.02615   0.01822  -0.0294   0.4071   0.9714
   5.750   0.8405   0.02628   0.01830  -0.0336   0.3975   0.9812
   6.000   0.8872   0.02602   0.01796  -0.0377   0.3839   0.9912
   6.250   0.9274   0.02556   0.01750  -0.0407   0.3682   1.0000
   6.500   0.9346   0.02565   0.01774  -0.0377   0.3598   1.0000
   6.750   0.9506   0.02577   0.01780  -0.0361   0.3544   1.0000
   7.000   0.9550   0.02606   0.01829  -0.0326   0.3471   1.0000
   7.250   0.9683   0.02593   0.01807  -0.0304   0.3389   1.0000
   7.500   0.9722   0.02611   0.01841  -0.0267   0.3312   1.0000
   7.750   0.9860   0.02615   0.01839  -0.0245   0.3249   1.0000
   8.000   0.9848   0.02592   0.01824  -0.0197   0.3135   1.0000
   8.250   0.9854   0.02604   0.01843  -0.0154   0.3055   1.0000
   8.500   0.9734   0.02539   0.01772  -0.0086   0.2881   1.0000
   8.750   0.9656   0.02519   0.01751  -0.0027   0.2729   1.0000
   9.000   0.9601   0.02522   0.01755   0.0028   0.2568   1.0000
   9.250   0.9561   0.02547   0.01778   0.0079   0.2399   1.0000
   9.500   0.9448   0.02590   0.01817   0.0141   0.2130   1.0000
   9.750   0.9299   0.02678   0.01885   0.0202   0.1719   1.0000
  10.000   0.9071   0.02865   0.02029   0.0260   0.1236   1.0000
  10.250   0.8786   0.03158   0.02280   0.0307   0.0647   1.0000
  10.500   0.8625   0.03427   0.02535   0.0334   0.0488   1.0000
  10.750   0.8520   0.03690   0.02799   0.0351   0.0432   1.0000
  11.000   0.8365   0.04031   0.03144   0.0363   0.0389   1.0000
  11.250   0.8231   0.04394   0.03517   0.0366   0.0364   1.0000
  11.500   0.8029   0.04870   0.04006   0.0362   0.0333   1.0000
  11.750   0.7939   0.05257   0.04409   0.0354   0.0330   1.0000
  12.000   0.7844   0.05670   0.04835   0.0344   0.0331   1.0000
  12.250   0.7738   0.06113   0.05294   0.0332   0.0327   1.0000
  12.500   0.7612   0.06595   0.05790   0.0318   0.0322   1.0000
  12.750   0.7447   0.07143   0.06354   0.0300   0.0307   1.0000
  13.000   0.7382   0.07564   0.06786   0.0287   0.0309   1.0000
  13.250   0.7284   0.08041   0.07276   0.0272   0.0307   1.0000
  13.500   0.7185   0.08528   0.07772   0.0256   0.0300   1.0000
  13.750   0.7104   0.08993   0.08246   0.0241   0.0292   1.0000
  14.000   0.7072   0.09387   0.08648   0.0229   0.0291   1.0000
  14.250   0.7065   0.09744   0.09012   0.0218   0.0291   1.0000
<< Back to US1000ROOT (us1000root-il)

Polar data table (+)

Polar graphs


<< Back to US1000ROOT (us1000root-il)