The modulus and poisson’s ratio of material is bound up with problems of buckling in curved panels. The material named 2060-T8E30 is applied in skins of fuselage panels. Applicability of critical shearstress coefficients curves of curved panels with the material 2060-T8E30 needs research. Based on Abaqus Buckle method in linear statics analysis, dozens types of curved panels with the material 2060-T8E30 were modeled. A comparison between numerical value of finite element analysis and critical shearstress coefficients curves was conducted. By analyzing errors, the results were attained that for the material 2060-T8E30,ks(critical shearstress coefficients of curved panels) curve of d/h=1.5 is relatively higher than KsFEA(ks of finite element analysis) and the error is below 15%.ks curve of d/h=2 is relatively higher than KsFEA and the error is below 20%.ks curve of d/h=3.5 is relatively higher than KsFEA and the error is below 35%. In case of normal parameters of fuselage structures of airplanes, as d/h=3.5 and Z≤20,ks curve has a good applicability when Z＜10 but is relatively higher than KsFEA, with the error below 20%, when 10＜Z≤20.