Blade solidity
Blade solidity is an important design parameter for the axial flow impeller and is defined as the ratio of blade chord length to spacing. Where In case of an axial flow impeller mean radius is defined in terms of hub (formula_4,inner radius) and tip radius (formula_5,outer radius) as : Blade solidity affects various turbomachinery parameters. So to vary those parameters one needs to vary blade solidity but there are some limitations imposed by Aspect ratio (wing) (span/chord), pitch. If an impeller has few blades i.e high pitch it will result in less lift force and in a similar  manner for more blades i.e. very low pitch, there will be high drag force. Blade solidity should not be confused with rotor solidity, which is the ratio of the total area of the rotor blades to the swept area of the rotor. Flow over isolated airfoil. Blade solidity is an important parameter that inter relates turbomachine parameter to airfoil parameter. Lift and drag coefficient for an airfoil is inter related to blade solidity as shown: where In an airfoil the mean line curvature is designed to change the flow direction, the vane thickness is for strength and the streamlined shape  is to delay the onset of boundary layer separation, taking all the design factors of an airfoil resulting forces of lift and drag can be expressed in terms of lift and drag coefficient. Preliminary design procedure. Design of the impeller depends on specific speed, hub-tip ratio and solidity ratio. To illustrate the dependence, an expression for axial flow pump and fan is shown where Cordier diagram can be used to determine specific speed and impeller tip diameter formula_23. Accordingly solidity ratio and hub-tip ratio (range 0.3-0.7) can be adjusted. Solidity ratio generally falls in the range of  0.4-1.1