Which of the following is the correct integrated range equation of cruise method 2?(a) R=\(\frac{1}{C}\Big(\frac{2W_i}{S_{\rho}}\Big)^{\frac{1}{2}}\frac{C_L}{C_D}2\Big(1-\omega^{\frac{-1}{2}}\Big)\)(b) R=\(\Big(\frac{2W_i}{S_{\rho}}\Big)^{\frac{1}{2}}\frac{C_{L}^{0.5}}{C_D}2\Big(1-\omega^{\frac{-1}{2}}\Big)\)(c) R=\(\frac{1}{C}\Big(\frac{2W_i}{S_{\rho}}\Big)^{\frac{1}{2}}\frac{C_{L}^{0.5}}{C_D}2\Big(1-\omega^{\frac{-1}{2}}\Big)\)(d) R=\(\frac{1}{C}\Big(\frac{2W_i}{S_{\rho}}\Big)^{\frac{1}{2}}\frac{C_{L}^{0.5}}{C_D}2\Big(1-\omega\Big)\)I had been asked this question during an internship interview.Asked question is from Cruise Method 2 topic in chapter Cruising Performance of Aircraft Performance

Which of the following is the correct integrated range equation of cru

1.	Which of the following is the correct integrated range equation of cruise method 2?(a) R=\(\frac{1}{C}\Big(\frac{2W_i}{S_{\rho}}\Big)^{\frac{1}{2}}\frac{C_L}{C_D}2\Big(1-\omega^{\frac{-1}{2}}\Big)\)(b) R=\(\Big(\frac{2W_i}{S_{\rho}}\Big)^{\frac{1}{2}}\frac{C_{L}^{0.5}}{C_D}2\Big(1-\omega^{\frac{-1}{2}}\Big)\)(c) R=\(\frac{1}{C}\Big(\frac{2W_i}{S_{\rho}}\Big)^{\frac{1}{2}}\frac{C_{L}^{0.5}}{C_D}2\Big(1-\omega^{\frac{-1}{2}}\Big)\)(d) R=\(\frac{1}{C}\Big(\frac{2W_i}{S_{\rho}}\Big)^{\frac{1}{2}}\frac{C_{L}^{0.5}}{C_D}2\Big(1-\omega\Big)\)I had been asked this question during an internship interview.Asked question is from Cruise Method 2 topic in chapter Cruising Performance of Aircraft Performance
Answer» The correct ANSWER is (c) R=\(\frac{1}{C}\Big(\frac{2W_i}{S_{\rho}}\Big)^{\frac{1}{2}}\frac{C_{L}^{0.5}}{C_D}2\Big(1-\omega^{\frac{-1}{2}}\Big)\) Explanation: The correct equation of CRUISE method 2 is R=\(\frac{1}{C}\Big(\frac{2W_i}{S_{\rho}}\Big)^{\frac{1}{2}}\frac{C_{L}^{0.5}}{C_D}2\Big(1-\omega^{\frac{-1}{2}}\Big)\) where R is range of the cruise, C is specific fuel CONSUMPTION, S is span, ρ is density, CL is coefficient of lift, Cl/Cd is ratio of coefficient of lift to drag, Wi is INITIAL weight and ω is fuel ratio.

Discussion

No Comment Found

Related InterviewSolutions

What is a trim in aircraft performance?(a) The state of equilibrium where the forces and moments are balanced(b) The state of equilibrium where the forces and moments are not balanced(c) The state of equilibrium where only the forces are balanced(d) The state of equilibrium where only the moments are balancedThis question was addressed to me in an interview for internship.This question is from Cruising Performance in portion Cruising Performance of Aircraft Performance
An aircraft is climbing with a 20° of climb angle and a 5° of angle of attack having a mass of 11,000 kg and aircraft thrust is 46082.75N then determine aircraft drag.(a) 33898.64 N(b) 52708.59 N(c) 82814.78 N(d) 8999.99 NI got this question in final exam.The query is from Cruising Performance in portion Cruising Performance of Aircraft Performance
In cruise performance the aircraft is considered to be steady, level, straight, symmetric flight with uniform acceleration.(a) True(b) FalseI have been asked this question in an internship interview.This is a very interesting question from Cruising Performance in portion Cruising Performance of Aircraft Performance
An aircraft is climbing with a 20° of climb angle and a 5° of angle of attack having a mass of 11,000 kg and aircraft drag is 9,000 N then determine engine thrust.(a) 5257.79 N(b) 1810.97 N(c) 28013.99 N(d) 46082.75 NThe question was posed to me in examination.I want to ask this question from Cruising Performance topic in section Cruising Performance of Aircraft Performance
An aircraft is climbing with a 20° of climb angle and a 5° of angle of attack having a mass of 11,000 kg and aircraft drag is 9,000 N then determine aircraft lift.(a) 11453.17 N(b) 9220.07 N(c) 11553.17 N(d) 97385.85 NI have been asked this question in class test.This interesting question is from Cruising Performance in chapter Cruising Performance of Aircraft Performance
What is specific air range?(a) horizontal distance flown per unit of fuel consumed(b) vertical distance flown per unit of fuel consumed(c) horizontal distance flown per unit time(d) vertical distance flown per unit timeI had been asked this question during an interview for a job.My query is from Cruising Performance topic in chapter Cruising Performance of Aircraft Performance
What will be the specific endurance of an aircraft having fuel mass flow 0.75 kg/s and true air speed is 300m/s?(a) 400 m/kg(b) 333 m/kg(c) 133 m/kg(d) 250 m/kgThe question was asked in quiz.This is a very interesting question from Cruising Performance topic in section Cruising Performance of Aircraft Performance
What will be the specific endurance of an aircraft having fuel mass flow 0.75 kg/s?(a) 4.33 s/kg(b) 3.33 s/kg(c) 1.33 s/kg(d) 2.33 s/kgThis question was posed to me by my college professor while I was bunking the class.Enquiry is from Cruising Performance in section Cruising Performance of Aircraft Performance
What is specific endurance?(a) It is instantaneous flight distance per unit of time(b) It is instantaneous flight time per unit of distance(c) It is instantaneous flight distance per unit of fuel consumed(d) It is instantaneous flight time per unit of fuel consumedThis question was posed to me in exam.I need to ask this question from Cruising Performance in chapter Cruising Performance of Aircraft Performance
In cruise performance the fuel mass flow determines the rate of change of mass of the aircraft.(a) True(b) FalseI had been asked this question in a national level competition.This interesting question is from Cruising Performance in chapter Cruising Performance of Aircraft Performance

Discussion

No Comment Found

Related InterviewSolutions

Reply to Comment