Calculate the basic performance for 'PA-28-161 PIPER WARRIOR III' aircraft at sea level on the earth: a/ Service ceiling

As I know the formula of the Service ceiling (photo attached), but I don’t know how to apply it specifically. Thank you so much.
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Here is the aircraft information and data:
- alpha = 0*pi/180 (Trim Angle of attack [rad]. This should be zero since)
- alpha_0 = -2.6*pi/180 (Airfoil zero-lift AOA [rad])
- Trim altitude [ft] = 0
- Aspect ratio of the wing = 7.2
- Span of the flap [ft] = 16.92 (Aileron total span)
- Span of the wing = 10.668 m
- Drag coefficient at zero lift (parasite drag) = 0.035
- 2-D maximum lift coefficient of wing = 6.22
- Cm_0_r = -0.072 (Zero lift pitching moment coefficient of the wing root)
- Cm_o_t = -0.072 (Zero lift pitching moment coefficient of the wing tip)
*** Cm_0_r = Cm_o_t because wing has no twist
- Mean aerodynamic chord of the wing [ft] = 4.846
- Oswald's efficiency factor (e_os) = 0.8333
- Weight of Airplane = 10846.44 N
- Power of the engine (Pe) = 119312
- Propeller efficiency (ηp) = 0.83
- Area of wing surface (s) = 15.806 m
- κ— proportionality constant = 1