A rotor blade of a turbine engine may have internal passages to permit the travel of cooling air through the blade. These passages may include a tip flag, a serpentine channel, and a trailing edge channel. The tip flag may extend radially outward along the leading edge of the rotor blade and may turn axially aftward along the tip of the rotor blade. The tip flag may terminate forward of a portion of the serpentine channel and the trailing edge channel. Thus the tip flag may be a “partial tip flag.” The internal passages may be arranged to ameliorate the effect of ambient pressure variations, such as between the leading edge and the trailing edge of the rotor blade, on the flow travel of cooling air through the rotor blade.