A blade for a gas turbine engine, comprising: an airfoil including pressure and suction side surfaces joined at leading and trailing edges to provide an exterior airfoil surface, the airfoil extending from a 0% span position at an inner flow path surface to a 100% span position at a tip, a mean camber line is provided at the tip and extends from the leading edge to the trailing edge, the mean camber line has a leading edge tangent line (T MCF) at the leading edge at the tip and a trailing edge tangent line (T MCR) at the trailing edge at the tip, the leading edge tangent line (T MCF) and the trailing edge tangent line (T MCR) intersect to provide a total camber angle (θ t ∗) in a range of -35° to 35°, wherein: the pressure side includes a tip shelf; the tip shelf wraps around the leading edge and includes cooling holes; the airfoil has a stagger angle (φ) that changes from the 0% span position to the 100% span position, a base region disposed adjacent to the attachment, a tip region, and a transition region located between the base and the tip regions, a rate of the change of the stagger angle (φ) in the transition region is greater than a rate of the change of the stagger angle (φ) in the base region, the rate of the change of the stagger angle (φ) in the transition region is greater than a rate of change of the stagger angle (φ) in the tip region, and the airfoil has a true chord that increases as the airfoil extends from the base region to the tip; the stagger angle rate of change between the attachment and the tip is represented by a first curvilinear relationship, and a true chord rate of change between the attachment and the tip is represented by a second curvilinear relationship, the transition region has a first point of inflection, where curvature of the first curvilinear relationship changes from a negative value to a positive value, and a second point of inflection, where curvature of the second curvilinear relationship changes from a negative value to a positive value; the tip includes a squealer pocket, and the squealer pocket includes purge holes; and the 100% span position includes a maximum thickness (TMAX 100) provided at a region beginning 20% from the leading edge and ending 20% from the trailing edge in a chord-wise direction. the pressure side includes a tip shelf; the tip shelf wraps around the leading edge and includes cooling holes; the airfoil has a stagger angle (φ) that changes from the 0% span position to the 100% span position, a base region disposed adjacent to the attachment, a tip region, and a transition region located between the base and the tip regions, a rate of the change of the stagger angle (φ) in the transition region is greater than a rate of the change of the stagger angle (φ) in the base region, the rate of the change of the stagger angle (φ) in the transition region is greater than a rate of change of the stagger angle (φ) in the tip region, and the airfoil has a true chord that increases as the airfoil extends from the base region to the tip; the stagger angle rate of change between the attachment and the tip is represented by a first curvilinear relationship, and a true chord rate of change between the attachment and the tip is represented by a second curvilinear relationship, the transition region has a first point of inflection, where curvature of the first curvilinear relationship changes from a negative value to a positive value, and a second point of inflection, where curvature of the second curvilinear relationship changes from a negative value to a positive value; the tip includes a squealer pocket, and the squealer pocket includes purge holes; and the 100% span position includes a maximum thickness (TMAX 100) provided at a region beginning 20% from the leading edge and ending 20% from the trailing edge in a chord-wise direction.