|
The NACA airfoils are airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA). The shape of the NACA airfoils is described using a series of digits following the word "NACA". The parameters in the numerical code can be entered into equations to precisely generate the cross-section of the airfoil and calculate its properties. ==Four-digit series== The NACA four-digit wing sections define the profile by:〔E.N. Jacobs, K.E. Ward, & R.M. Pinkerton. (NACA Report No. 460, "The characteristics of 78 related airfoil sections from tests in the variable-density wind tunnel" ). NACA, 1933.〕 # First digit describing maximum camber as percentage of the chord. # Second digit describing the distance of maximum camber from the airfoil leading edge in tens of percents of the chord. # Last two digits describing maximum thickness of the airfoil as percent of the chord.〔"Fundamentals of aerodynamics", John D. Anderson,Jr, third ed, chap 4〕 For example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord. Four-digit series airfoils by default have maximum thickness at 30% of the chord (0.3 chords) from the leading edge. The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long. 抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』 ■ウィキペディアで「NACA airfoil」の詳細全文を読む スポンサード リンク
|