Problem Statement 2 The newly designed Raptor Rocket Engine by Elon Musk's "SpaceX" utilizes liquid methane (CH4(l)) as the propellant and liquid oxygen (O2(l)) as the oxidizer. The thrust produced by the Raptor is related to the flow rate of the propellant and the oxidizer. An experimental observation is carried out by taking different mixtures of the propellant (P) and oxidizer (X) and the Net Thrust (T) is recorded for different settings. The observed data is as follows: (a) As an Engineer you are tasked to establish a quadratic relationship (in the form of: y(x1,x2)=A0+A1x12+A2x22+A3x1x2) between the net thrust (y=T) and the propellant-oxidizer (x1=P and x2=Q ) flow rates using suitable regression method using the above data. Estimate the standard error of your model to verify the performance of your model. Use suitable Python Program to develop and evaluate the model. (b) The existing turbo pumps at SpaceX can hypothetically produce a maximum O2 (l) flow rate of 900kg/sec and CH4(l) flow rate of 250kg/sec. Without going on to the test bench again, can you utilize your obtained relationships in the previous step to predict the Net Thrust at the Maximum Settings of the turbo pumps