Using Python 3.7 not using any powerful modules

2. (25 points) The following describes a tiny part points) ine following describes a tiny part of the airplane design process - Choosing the engine size needed to meet a take-off distance requirement (Sto). Sto is the distance distance requirement (STO). Sto is the distance an airplane will roll on the is able to lift off into the air. Calculating Sto is performed using a sequence of five equations shown below. Those equations require seven paramet ow. Those equations require seven parameters that control takeoff performance. The engine thrust parameter is a major factor in determini rust parameter is a major factor in determining take-off distance. The graph shows how take-off distance gets shorter as engine thrust is increased. Weight stall tho S.CLmas Thrust - 13000 Weight - 56000 $ - 1000 CLmas - 24 CD - 0.0279 rho - 0.002377 ge = 322 VTO - 1.2 Vstau 6000 Agc Thrust Weight 4000F Sto thrust) 2000F TO STO 10000 A-Bv thrust Write a Python program that includes and calls the following three functions: def STO(thrust): Thrust the value of the engine thrust. Important, this is the only argument to be passed to this function. All of the other required airplane parameters may be assumed constant. Local variables for those parameters may be defined and assigned values inside the STO function. Use the airplane parameter values given in the figure above. The function calculates and returns: the airplane take-off distance, calculated using the five equations given above. The first four of those equations calculate the value of three constants to be used in the fifth equation (VTO, A and B). That fifth equation requires the use of numerical integration. Use your Simpson function to perform the integration. This problem statement is continued on the next page. FTUDIILIL def ThrustNeeded ForTakeoff(distance): distance: the required take-off distance. Important this is the only argument to be passed to this function. All of the other required airplane parameters may be assumed al variables for those parameters may be defined and assigned values inside the ThrustNeeded For Takeoff function. Use the airplane parameter values given in the figure on the previous page. le function calculates and returns: the engine thrust needed to allow the airplane to take-off in the specified distance. Hint: The ThrustNeeded For Takeoff function behaves as the inverse of the STO function. Therefore it must use a root-finding method to find the value of thrust that causes: STO(thrust) - distance = 0 Use your Secant function so solve for this value of thrust. c) def main(): main() has no arguments and no return value. main() does the following: a) calls STO(13000) to calculate the take-off distance for an engine thrust of 13000 pounds. Print the answer with one decimal place, using a nice text label. The nice text label should include the thrust value of 13000 pounds. b) calls ThrustNeeded ForTakeoff(1500) to calculate the thrust needed to allow takeoff in 1500 feet. Print the answer with two decimal places, using a nice text label. The nice text label should include the takeoff distance of 1500 feet. c) calls ThrustNeeded For Takeof(1000) to calculate the thrust needed to allow takeoff in 1000 feet. Print the answer with two decimal places, using a nice text label. The nice text label should include the takeoff distance of 1000 feet. You will name this program Problem 2.py, and upload it to the Exam 1 - Part 2 Brightspace Dropbox. 2. (25 points) The following describes a tiny part points) ine following describes a tiny part of the airplane design process - Choosing the engine size needed to meet a take-off distance requirement (Sto). Sto is the distance distance requirement (STO). Sto is the distance an airplane will roll on the is able to lift off into the air. Calculating Sto is performed using a sequence of five equations shown below. Those equations require seven paramet ow. Those equations require seven parameters that control takeoff performance. The engine thrust parameter is a major factor in determini rust parameter is a major factor in determining take-off distance. The graph shows how take-off distance gets shorter as engine thrust is increased. Weight stall tho S.CLmas Thrust - 13000 Weight - 56000 $ - 1000 CLmas - 24 CD - 0.0279 rho - 0.002377 ge = 322 VTO - 1.2 Vstau 6000 Agc Thrust Weight 4000F Sto thrust) 2000F TO STO 10000 A-Bv thrust Write a Python program that includes and calls the following three functions: def STO(thrust): Thrust the value of the engine thrust. Important, this is the only argument to be passed to this function. All of the other required airplane parameters may be assumed constant. Local variables for those parameters may be defined and assigned values inside the STO function. Use the airplane parameter values given in the figure above. The function calculates and returns: the airplane take-off distance, calculated using the five equations given above. The first four of those equations calculate the value of three constants to be used in the fifth equation (VTO, A and B). That fifth equation requires the use of numerical integration. Use your Simpson function to perform the integration. This problem statement is continued on the next page. FTUDIILIL def ThrustNeeded ForTakeoff(distance): distance: the required take-off distance. Important this is the only argument to be passed to this function. All of the other required airplane parameters may be assumed al variables for those parameters may be defined and assigned values inside the ThrustNeeded For Takeoff function. Use the airplane parameter values given in the figure on the previous page. le function calculates and returns: the engine thrust needed to allow the airplane to take-off in the specified distance. Hint: The ThrustNeeded For Takeoff function behaves as the inverse of the STO function. Therefore it must use a root-finding method to find the value of thrust that causes: STO(thrust) - distance = 0 Use your Secant function so solve for this value of thrust. c) def main(): main() has no arguments and no return value. main() does the following: a) calls STO(13000) to calculate the take-off distance for an engine thrust of 13000 pounds. Print the answer with one decimal place, using a nice text label. The nice text label should include the thrust value of 13000 pounds. b) calls ThrustNeeded ForTakeoff(1500) to calculate the thrust needed to allow takeoff in 1500 feet. Print the answer with two decimal places, using a nice text label. The nice text label should include the takeoff distance of 1500 feet. c) calls ThrustNeeded For Takeof(1000) to calculate the thrust needed to allow takeoff in 1000 feet. Print the answer with two decimal places, using a nice text label. The nice text label should include the takeoff distance of 1000 feet. You will name this program Problem 2.py, and upload it to the Exam 1 - Part 2 Brightspace Dropbox