center of mass for naca airfoil

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 February 14, 2002, 20:01 center of mass for naca airfoil #1 frederic Felten Guest   Posts: n/a Hi, there, I'm seeking the coordinates of the center of gravity (center of mass, not aerodynamic center, or center of pressure !!) for the naca 0018 airfoil. I already spent some time checking the resources available from cfd-online, and nowhere was i able to find this info! If you do have such info, please let me know. Sincerely, Frederic Felten. amin013 likes this.

 February 16, 2002, 08:40 Re: center of mass for naca airfoil #2 FYW Guest   Posts: n/a From the generic definition of CG, knowing the coordiates of the airfoil, you can calculate it.

 February 16, 2002, 13:56 Re: center of mass for naca airfoil #3 Srinivasan Guest   Posts: n/a Hi! Frederic, If you assume homogeneous mass distribution, the coords of the center of gravity is the average of the coords of the airfoil contour, isn't it? If you don't have homogeneous mass distribution, then the center is caculcated as r_cg = sum_over_i( m_i r_i) / sum_over_i(m_i) where r_cg and r_i are vectors. Basically, homogeneous mass distribution means all m_i are equal, which reduces to the average of r_i. Hope this helps Srinivasan

 February 20, 2002, 11:55 Re: center of mass for naca airfoil #4 Patrick Hanley, Ph.D. Guest   Posts: n/a Dear Mr. Felten, I used my WingAnalysis Plus Cross Section Tool to obtain a position of the CG for the NACA 0018 at about 42% chord from the leading edge (along the mean chord line). Regards, Patrick Hanley, Ph.D. Aerodynamics Software http://www.hanleyinnovations.com

 November 15, 2016, 11:24 #5 Senior Member     Louis Gagnon Join Date: Mar 2009 Location: Stuttgart, Germany Posts: 338 Rep Power: 18 For those looking for an answer to this simple but interesting question, for all NACA symmetric airfoils, with the closed trailing edge, the center of mass is at roughly 0.3994*chord from the leading edge. If the trailing edge is "open" (last coefficient is -0.1015) then the center of mass is at roughly 0.4015*chord. This results from the calculation shown here: http://louisgagnon.com/scBlog/airfoilCenter.html amin013 likes this.

 Tags naca 0018, naca blade profile