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# aeronautical engineering - base level watch

1. the question is :
Calculate the cruise altitude of anGulfstream IV in feet.
For Gulfstream IV. The following data on this aircraft is given.
• Number of engines: 2
• Wing surface: S=88.3 m2
• Diameter of engine inlet: d=1.1176 m
• Oswald efficiency: e=0.67
• Span: b=23.7 m
• Mass: m=30000 kg
• (ISA) Air density at cruise altitude: ρ=0.42 kg/m3
• Cruise speed: VTAS=460 kts
• Zero-lift drag coefficient: CD0=0.015
For the International Standard Atmosphere (ISA) please use:
• Gravity acceleration: g=9.80665 m/s2
• Gas constant for air: R=287.00 J/ kgK
• Sea-level pressure: p0=101325 Pa
• Sea-level temperature: T0=15∘C
• Sea-level density: ρ0=1.225 kg/m3

I've tried to solve it as follow:

P= rho*R*T
R=287
rho is given=0.42
T means Temperature (it is not given )
P means pressure
So I want to get the value of P from the above equation in order to use it in the following equation in order to find the altitude:
P= rho*h*g
So I can get the value of h (altitude) h=p/(rho*g)
but still T in the previous equation is unknown,
so anyone can help with this question pls

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