Stress evolution in thermal barrier coatings for rocket engine applications

Table 2 Material data for NiCrAlY

Thermal Conductivity / W/m K (Altun et al. 2008; Pawlowski 2008)	Temp /K
12	800
17	1300
Coefficient of thermal expansion (Taylor and Walsh 2004) / K ⁻¹	Temp /K
13.0×10⁻⁶	400
12.9×10⁻⁶	500
13.1×10⁻⁶	600
13.4×10⁻⁶	700
13.7×10⁻⁶	800
14.0×10⁻⁶	900
14.3×10⁻⁶	1000
15.6×10⁻⁶	1100
19.0×10⁻⁶	1400
Specific Heat * / J/kg K	Temp
460	343.14
410	473.14
330	673.14
230	873.14
400	1073.14
1440	1273.14
1370	1373.14
Density / kg/m³
6.9×10³
Young’s modulus (Margadant et al. 2006) / GPa	Poisson’s ratio (Taylor and Bettridge 1996)	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
1200	294.14
1200	773.14
900	873.14
380	973.14
100	1073.14
60	1173.14