Root_Airfoil.txt

(1 KB) Pobierz
E205  (12.48%)
     1.000000   -0.000222
     0.996550    0.000135
     0.986490    0.001437
     0.970490    0.003957
     0.949160    0.007466
     0.922850    0.011578
     0.891750    0.016137
     0.856240    0.021219
     0.816839    0.026824
     0.774119    0.032865
     0.728659    0.039256
     0.681079    0.045850
     0.632039    0.052499
     0.582179    0.059018
     0.532169    0.065166
     0.482649    0.070636
     0.434099    0.075042
     0.386799    0.078109
     0.341009    0.079679
     0.296989    0.079675
     0.254959    0.078080
     0.215080    0.074994
     0.177640    0.070627
     0.143020    0.065157
     0.111570    0.058711
     0.083601    0.051428
     0.059371    0.043439
     0.039091    0.034934
     0.022921    0.026075
     0.010971    0.017149
     0.003311    0.008640
     0.000020    0.000324
     0.002329   -0.006410
     0.010648   -0.013490
     0.024187   -0.020279
     0.042905   -0.026408
     0.066684   -0.031753
     0.095332   -0.036242
     0.128631   -0.039845
     0.166260   -0.042532
     0.207819   -0.044311
     0.252888   -0.045166
     0.300958   -0.045053
     0.351478   -0.043991
     0.403868   -0.042072
     0.457499   -0.039427
     0.511729   -0.036233
     0.565900   -0.032712
     0.619371   -0.029057
     0.671483   -0.025405
     0.721594   -0.021848
     0.769105   -0.018455
     0.813426   -0.015284
     0.853997   -0.012357
     0.890337   -0.009693
     0.921948   -0.007220
     0.948599   -0.004817
     0.970169   -0.002626
     0.986350   -0.001068
     0.996510   -0.000366
     1.000000   -0.000222
Zgłoś jeśli naruszono regulamin