Some important parameters to describe an airfoil's shape are its camber and its thickness. For example, an airfoil of the NACA 4-digit series such as the NACA 2415 (to be read as 2 – 4 – 15) describes an airfoil with a camber of 0.02 chord located at 0.40 chord, with 0.15 chord of maximum thickness.

2022年5月18日 · The thickness of the airfoil is a very important design parameter and as always expressed as a percentage of the total chord. The airfoil plotted above has a thickness-to-chord ratio of 12%. This means that the height at the thickest section is equal to 12% of the total chord.

2019年8月5日 · Factors for determining the wing thickness during the aeroplane design procedure: Determine the required structure height, which follows from the aspect ratio determined by the aerodynamicists: the cantilever ratio, which is the structural wing semi-span divided by maximum root thickness.

•The high thickness and camber produce low critical Mach numbers. •Consider the maximum section lift coefficients for several different thickness-ratio airfoils presented in the table. •The data show that a low-speed airfoil has an optimum thickness for maximizing the lift of the airfoil.

maximum distance from the chord line to the camber line is designated as the airfoil camber ( ), generally expressed as a percent of the chord line, such as 5% camber. The maximum distance between the upper and lower surface is the airfoil thickness, , also designate as a percent of chord length. The we have: (1)

The airfoil has a thickness-to-chord ratio of 11.7% and is flat on the lower surface aft of 30% chord. The Clark Y gives reasonable overall aerodynamic performance but is rarely used in modern designs.

2024年4月16日 · Maximum Thickness. Thickness distribution on airfoil gives it aerodynamic shape and helps improve the flow separation characteristics. A maximum thickness ratio (t/c) of airfoil (also defined in terms of the percentage of the cord) has a …

Maximum Thickness: Maximum distance between the upper and lower surfaces of the airfoil normal to the chord line. Span: Width of the airfoil. Angle of Attack: Angle between the chord line and the streamwise flow direction. Zero Lift Angle of Attack: Angle of …

Methods for airfoil design can be classified into two categories: direct and inverse design. The direct airfoil design methods involve the specification of section geometry and the calculation of pressures and performance. One evaluates the given shape and then modifies the shape to improve the performance.

The last two digits determine the thickness of the airfoil. Thus the higher the number, the thicker the airfoil. The maximum thickness of these airfoils is 12%, 24%, and 36% of their chord length, respectively.