Rotor blade for a turbomachine

A rotor blade for arrangement in a gas duct of a turbomachine, wherein the rotor blade comprises a rotor blade airfoil which, when viewed in a tangential section, has a blade airfoil profile comprising

• a front edge radius RVK, and
• a blade airfoil thickness d,
• the blade airfoil profile being thickened at least in sections, and the blade airfoil thickness d being set with respect to the front edge radius RVK such that at least at a spacing A of 1 mm or 0.5 mm, measured along a skeletal line of the blade airfoil from the front edge thereof,
• (2×d/RVK2)−d≤5.5
• and wherein:
• i) the blade airfoil thickness d in a front edge region at the spacing A is from 0.5 mm to 5 mm;
• and/or
• (ii) in terms of a chord length l measured on the blade airfoil profile, the blade airfoil thickness d is set at a ratio to the front edge radius RVK and the chord length l such that 4.0≤d/(RVK×1)≤7.0;
• and/or
• iii) in terms of the chord length 1 measured on the blade airfoil profile, at least at the spacing A between 1.0 mm and 2.0 mm that is measured along the skeletal line of the blade airfoil profile from the front edge thereof, the blade airfoil thickness d is set with respect to the front edge radius RVK and the chord length 1 such that d/(RVK×1)≤7.2;
• and/or
• iv) the blade airfoil thickness d is set with respect to the front edge radius RVK such that 0.6≤(2×d/RVK2)−d≤4.0.