The protection of the combustion wall chamber of aeronautic propeller is assumed with a full coverage film cooling. In the case of 1-9 rows of eight staggered holes, we have measured several profiles of temperature in the mainstream perturbed by jets. Variations of wall temperatures T-p have been measured simultaneously along the wall. Those experiences have been performed for three thermal cases, which are a function of the mainstream temperature T., the injected temperature T-i and the electrical density phi(dissi). imposed at the wall. Three blowing rates M = rho(i)U(i)/rho(e)U(e) are imposed too. The results are compared with the reference case without holes. The exam of the temperature profiles allows us to find a minimum number of rows to create a homogeneous cold layer. Two schemes of the convective heat transfer with two coefficients are presented and allow to represent each of the three thermal cases for the three blowing rates. Those models take into account of the three characteristic temperatures (T,, Ti and Tp). One model is studied for 9 rows with infrared thermography. For five blowing rates, four zones of variations and an influence of M on the two coefficients are underlined. (C) 2003 Elsevier Science Ltd. All rights reserved.