Question

Anyone happen to know how to write the MATLAB code for this? It's an aerospace engineering problem and I'm super confused, any help would be greatly appreciated!

105 100 225.66 K G4 = 4 X 10-3 K/m 90 80 79 165.66 K аз--4.5 x 10-3 K/m 60 ー53 а» 40 282.66 K a2-3 x 10-3 K/m 25 20 ai--6.5 X 10-3 K/im 216.66 K 288.16 K 0 160 200 240 280 320 Temperature, K For isothermal regions of the atmosphere, the properties can be found if the temperature, pressure, and density are known at the base (bottom) of the layer. If these properties have the values T1, pl, and ρ1 at height hi, then the values at a height h > h1 (but still within the isothermal layer) are found as T(h) T1 RT where go is sea level gravity of 9.807 m/s2 and R is the specific gas constant (287 J/kg/K). For gradient regions of the atmosphere, the properties depend on the thermal gradient a - dT/dh. If the properties at the base of the layer have the values T, , pi, and ρ, at height hi, then the values at a height h > hi (but still within the gradient layer) are found as: go aR aR T. The standard atmosphere is made up of the 7 regions shown on page 1 (3 isothermal regions and 4 gradient regions), as follows: 0

Answer 1

-on 9:-6.se.. 3 ' . J. Ryên l Сны Tq = 크16 .coy. Rion 2 (k)

h1: 9025,

p*T2

end

O. 1261 1O60 ひ 43.GCo ㄑㄧ Tho ไว้000) 15.660 ho 6.38518-07

ㄩ〇 2 0 190 60 1ぬ 60