Stress evolution in thermal barrier coatings for rocket engine applications

Table 3 Material data for NiCrCuAl

Thermal Conductivity † / W/m K	Temp / K
12	800
17	1300
Coefficient of thermal expansion (Fiedler et al. 2014) / K ⁻¹	Temp / K
13.7×10⁻⁶	323.14
14.6×10⁻⁶	423.14
14.9×10⁻⁶	523.14
14.6×10⁻⁶	623.14
14.2×10⁻⁶	723.14
14.3×10⁻⁶	823.14
14.8×10⁻⁶	923.14
16.0×10⁻⁶	1023.14
17.7×10⁻⁶	1123.14
18.9×10⁻⁶	1223.14
19.9×10⁻⁶	1323.14
20.46×10⁻⁶	1393.14
Specific Heat * / J/kg K	Temp
480	293.14
490	400
460	600
400	700
350	800
370	900
400	950
530	1000
630	1050
620	1100
630	1200
Density * / kg/m³
7.7×10⁺³
Young’s modulus † / GPa	Poisson’s ratio	Temp / K
120	0.3	293.14
100	0.3	673.14
80	0.3	1073.14
70	0.3	1273.14
Yield stress * /MPa	Temp / K
1100	294.14
1000	473.14
790	773.14
540	823.14
160	873.14
70	973.14
60	1073.14

Data labelled with an asterisk are based on own unpublished measurements, data labelled with a dagger are assumed to be identical to NiCrAlY