AT 106 Exam 2 Actual Questions and Answers 2024 Graded A

AT 106 Exam 2 Actual Questions and Answers 2024 Graded A How is yaw controlled on a flying wing aircraft? A) A primary flight control attached to the rear of the vertical stabilizer. B) Differential engine thrust C) Split "Drag" rudders at the wing tips D) None of the above - Answer ️️ -C) The control surface primarily responsible for roll control in a flying wing is which of the following? A) Elevators B) Aileron C) Split "Drag" rudders at the wing tips D) Elevon - Answer ️️ -C) The control surface primarily responsible for pitch control in a flying wing is which of the following? A) Elevators B) Aileron C) Split "Drag" rudders at the wing tips D) Elevon - Answer ️️ -B) How is yaw stability obtained in a flying wing aircraft? A) Horizontal Stabilizer B) Vertical Stabilizer C) Swept back wings D) Split "Drag" rudders at the wing tips - Answer ️️ -C) What is true of the longitudinal center of gravity range on a flying wing aircraft? A) The CG range is less than a conventional tailed aircraft B) The CG range is greater than a conventional tailed aircraft C) The CG range is the same as on a conventional tailed aircraft - Answer ️️ -A) Which of the following is true of a flying wing aircraft? A) The horizontal stabilizer function has been eliminated B) The Split "Drag" rudders replace the standard horizontal tail C) The horizontal stabilizer is the same as on conventional tailed aircraft D)The horizontal stabilizer function has been incorporated into the wing near the wing root - Answer ️️ -A) Which of the following is not true? A) A flying wing aircraft has less total induced drag than a conventional tailed aircraft B) A flying wing is more stable than a conventional tailed aircraft C) A flying wing aircraft has less skin friction drag than a conventional tailed aircraft D) A flying wing aircraft has all of the same rudder and elevator functions of a conventional tailed aircraft - Answer ️️ -C) Which of the formulas below accurately represent Mach Number? A) True Speed of aircraft / Speed of Sound = Mach Number B) True Speed of aircraft * Speed of Sound = Mach Number C) Speed of Sound / True speed of aircraft = Mach Number D) Speed of Sound * True speed of aircraft = Mach Number - Answer ️️ -A) When does the transonic range begin? A) At 0.79 M B) At 1.0 M C) At the first evidence of localized sonic flows around the aircraft D) At the point where the compressibility index reaches 1.0 - Answer ️️ -C) What is Mach Critica