The thrust equation is presented not as a single number, but as: $$F = \dotm_c \left[(1+f)V_9 - V_0\right] + \dotm f \left(V 19 - V_0\right)$$ Each component is calculated in a separate row, ending with $F/\dotm_0 = 625.4 \text N/(kg/s)$.
For those looking for official resources, many universities provide access to instructor-approved materials through platforms like (the book's publisher) or academic portals. Conclusion
Solutions for or 8 (Axial Compressor Aerodynamics) . Specific examples like problem 2.4 (oblique shocks) . Let me know which chapter you're working on. Aircraft Propulsion Saeed Farokhi