Question 3The aerodynamic derivative X, may be determined from the following expression:X-pU SCD%3Dwhere p is the air density, S is the wing area, U is the airspeed, and Cp is the drag coefficient.Consider an aircraft of weight 68 kN and wing area 43 m?, flying straight and level under internationalstandard atmosphere (ISA) conditions, where p 1.018 kg/m, at an airspeed of 155 m/s. The aircraft%3Dhas a drag polarCp = 0.011 +where Ci is the lift coefficient.Calculate the value of X, at this flight condition. Give your answer in units of Ns/m.

aerodynamic derivative X, may be determined from the following expression: X =-pU SCD %3D nere pis the air density, S is the wing area, U is the airspeed, and Cp is the drag coefficient. consider an aircraft of weight 68 kN and wing area 43 m2, flying straight and level under internationa tandard atmosphere (ISA) conditions, where p = 1.018 kg/m³, at an airspeed of 155 m/s. The aircraft has a drag polar %3D Cp 0.011 + 0.15C7 where CL is the lift coefficient. Calculate the value of X, at this flight condition. Give your answer in units of Ns/m.

aerodynamic derivative X, may be determined from the following expression: X =-pU SCD %3D nere pis the air density, S is the wing area, U is the airspeed, and Cp is the drag coefficient. consider an aircraft of weight 68 kN and wing area 43 m2, flying straight and level under internationa tandard atmosphere (ISA) conditions, where p = 1.018 kg/m³, at an airspeed of 155 m/s. The aircraft has a drag polar %3D Cp 0.011 + 0.15C7 where CL is the lift coefficient. Calculate the value of X, at this flight condition. Give your answer in units of Ns/m.

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.9P: When a sphere falls freely through a homogeneous fluid, it reaches a terminal velocity at which the...

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