The paper considers a temperature boundary layer in a flat laminar incompressible flow past a heat-impermeable wall with continuously distributed pores on the surface through which fluid is sucked or blown. To solve this problem, the multiparametric method of L. G. Loitsyansky [1] improved by us in work [2] is used. Universal solutions determined by the numerical method for Prantl numbers: $Pr=1.0$ and $Pr=0.72$ are used to calculate the temperature boundary layer on a cylinder of a circle section and on a standard airfield with the designation NACA 0010-34.