An aerodynamic formulation has been developed to estimate the aerodynamic loads on a blade in a cascade of slightly cambered airfoils based on Whitehead?s aerodynamic theory for cascade of flat plates. The stability of the blade is determined by solving the structural model by posing it as a complex eigenvalue problem. It is shown that the flutter velocities in the bending mode get reduced by significant margin upon the inclusion of the camber. A possible explanation is that, as the blade camber increases, the lift force experienced by the blade in the heaving direction increases due to increased loading. This makes the blade more prone to bending flutter. Also, from the flutter boundaries for cambered blades, for values of the frequency ratio moved from unity, the flutter velocity increases in the torsional mode. This means that when a cambered blade with a significant difference in bending and torsional stiffness is employed for operation torsional flutter occurs only at higher air velocities, and at lower air velocities, the structure is prone to bending flutter. At frequency ratios near unity, the flutter velocities in the bending mode and torsional mode overlap, resulting in coupled bending?torsion flutter of the blade.