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 (MCL) is provided at the tip and extends from the leading edge to the trailing edge , the mean camber line (MCL) 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. <EOS>