1.8 Aerodynamics Quiz_ ASCI 121 Private Pilot Operations - Mar 2024 - Online

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3/24/24, 1:22 PM 1.8 Aerodynamics Quiz: ASCI 121 Private Pilot Operations - Mar 2024 - Online https://erau.instructure.com/courses/170679/quizzes/599641 1/7 Due Mar 24 at 11:59pm Points 100 Questions 25 Time Limit 50 Minutes Instructions Attempt History Attempt Time Score LATEST Attempt 1 29 minutes 100 out of 100  Correct answers are hidden. Score for this quiz: 100 out of 100 Submitted Mar 24 at 4:22pm This attempt took 29 minutes.  Question 1 4 / 4 pts attack. dihedral. 1.8 Aerodynamics Quiz Instructions: This quiz can only be taken once . Answer the 25 multiple choice questions in the time provided. Before you begin, make sure you have downloaded the FAA Airman Knowledge Testing Supplement Document (PDF) (https://www.faa.gov/training_testing/testing/supplements/media/sport_rec_private_akts.pdf) and are familiar with navigating its contents, as some of the quiz questions will reference its figures. Any reference to a figure in the quiz can be found in the Supplement Document. Time limit: There is a 50-minute limit and at the end of 50 minutes, the exam will close and be automatically submitted for grading. You will get a notification pop-up approximately 10 seconds before time expires. If you leave the exam for any reason, the timer will continue and the exam will automatically submit when time is up. If you lose your Internet connection, you may reconnect and return to the exam where you left off as long as time has not expired. If you encounter technical difficulties, please contact your instructor. Grading: You will see scores for multiple-choice questions right away. Please contact your instructor if you have any questions. (Refer to Figure 1.) The acute angle A is the angle of

3/24/24, 1:22 PM 1.8 Aerodynamics Quiz: ASCI 121 Private Pilot Operations - Mar 2024 - Online https://erau.instructure.com/courses/170679/quizzes/599641 2/7 incidence. The angle of attack is the acute angle between the relative wind and the chord line of the wing.  Question 2 4 / 4 pts lift, weight, thrust, and drag. lift, weight, gravity, and thrust. lift, gravity, power, and friction. Lift, weight, thrust, and drag are the four basic aerodynamic forces acting on an aircraft in flight.  Question 3 4 / 4 pts be more difficult to control. stall at a higher airspeed. have a tendency to spin. Stall speed increases in proportion to the square root of the load factor. Thus, with a load factor of 4, an aircraft will stall at a speed which is double the normal stall speed.  Question 4 4 / 4 pts Inability to get airborne even though airspeed is sufficient for normal takeoff needs. Settling to the surface abruptly during landing. Becoming airborne before reaching recommended takeoff speed. Due to the reduced drag in ground effect, the airplane may seem capable of takeoff well below the recommended speed. It is important that no attempt be made to force the airplane to become airborne with a deficiency of speed. The recommended takeoff speed is necessary to provide adequate initial climb performance.  Question 5 4 / 4 pts heavily loaded. developing lift. operating at high airspeeds. Lift is generated by the creation of a pressure differential over the wing surface. The lowest pressure occurs over the wing surface and the highest pressure occurs under the wing. This pressure differential triggers the roll up of the airflow aft of the wing, resulting in wing-tip vortices. Vortices are generated from the moment an aircraft leaves the ground, since trailing vortices are a by-product of wing lift.  The four forces acting on an airplane in flight are During an approach to a stall, an increased load factor will cause the airplane to Ground effect is most likely to result in which problem? Wingtip vortices are created only when an aircraft is

3/24/24, 1:22 PM 1.8 Aerodynamics Quiz: ASCI 121 Private Pilot Operations - Mar 2024 - Online https://erau.instructure.com/courses/170679/quizzes/599641 3/7 Question 6 4 / 4 pts rise into the traffic pattern. sink below the aircraft generating turbulence. rise into the takeoff or landing path of a crossing runway. Flight tests have shown that the vortices from large aircraft sink at a rate of about 400 to 500 feet per minute. They tend to level off at a distance about 900 feet below the path of the generating aircraft.  Question 7 4 / 4 pts The location of the CG with respect to the center of lift. The effectiveness of the horizontal stabilizer, rudder, and rudder trim tab. The relationship of thrust and lift to weight and drag. The location of the center of gravity with respect to the center of lift determines to a great extent the longitudinal stability of an airplane. Center of gravity aft of the center of lift will result in an undesirable pitch-up moment during flight. An airplane with the center of gravity forward of the center of lift will pitch down when power is reduced. This will increase the airspeed and the downward force on the elevators. This increased downward force on the elevators will bring the nose up, providing positive stability. The farther forward the CG is, the more stable the airplane.  Question 8 4 / 4 pts lift/drag ratio. lifting capacity. aerodynamic balance and controllability. The center of pressure of an asymmetrical airfoil moves forward as the angle of attack is increased, and backward as the angle of attack is decreased. This backward and forward movement of the point at which lift acts, affects the aerodynamic balance and the controllability of the aircraft.  Question 9 4 / 4 pts above and upwind from the heavy aircraft. below and downwind from the heavy aircraft. below and upwind from the heavy aircraft. When departing behind a large aircraft, note the large aircraft's rotation point, rotate prior to it, continue to climb above it, and request permission to deviate upwind of the large aircraft's climb path until turning clear of the aircraft's wake.  Question 10 4 / 4 pts Wingtip vortices created by large aircraft tend to What determines the longitudinal stability of an airplane? Changes in the center of pressure of a wing affect the aircraft`s When departing behind a heavy aircraft, the pilot should avoid wake turbulence by maneuvering the aircraft

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3/24/24, 1:22 PM 1.8 Aerodynamics Quiz: ASCI 121 Private Pilot Operations - Mar 2024 - Online https://erau.instructure.com/courses/170679/quizzes/599641 4/7 Induced drag decreases; therefore, any excess speed at the point of flare may cause considerable floating. Wingtip vortices increase creating wake turbulence problems for arriving and departing aircraft. A full stall landing will require less up elevator deflection than would a full stall when done free of ground effect. The reduction of the wing-tip vortices, due to ground effect, alters the spanwise lift distribution and reduces the induced angle of attack, and induced drag causing floating.  Question 11 4 / 4 pts Corners 2 and 4. Corners 1 and 2. Corners 1 and 4. The airplane will turn less than 90 degrees at corners 1 and 4. At corner 1, the airplane turns to a heading that is crabbed into the wind, which makes the turn less than 90 degrees. At corner 4, the airplane is crabbed into the wind when the turn is started, and the turn will be less than 90 degrees.  Question 12 4 / 4 pts groundspeed at touchdown, a shorter ground roll, and the likelihood of undershooting the desired touchdown point. airspeed at touchdown, a longer ground roll, and better control throughout the landing roll. groundspeed at touchdown, a longer ground roll, and the likelihood of overshooting the desired touchdown point. A downwind landing, using the same airspeed as is used on a normal upwind landing, will result in a higher approach ground speed, with the likelihood of overshooting the desired touchdown point. The ground speed at touchdown will be higher than normal, and the ground roll will be longer.  Question 13 4 / 4 pts difficulty in recovering from a stalled condition. stalling at higher-than-normal airspeed. a longer takeoff run. Loading in a tail-heavy condition can reduce the airplane's ability to recover from stalls and spins. Tail-heavy loading also produces very light stick forces, making it easy for the pilot to inadvertently overstress the airplane.  Question 14 4 / 4 pts a higher-than-normal angle of attack. What must a pilot be aware of as a result of ground effect? (Refer to figure 62.) In flying the rectangular course, when would the aircraft be turned less than 90°? If an emergency situation requires a downwind landing, pilots should expect a faster An airplane has been loaded in such a manner that the CG is located aft of the aft CG limit. One undesirable flight characteristic a pilot might experience with this airplane would be Floating caused by the phenomenon of ground effect will be most realized during an approach to land when at

3/24/24, 1:22 PM 1.8 Aerodynamics Quiz: ASCI 121 Private Pilot Operations - Mar 2024 - Online https://erau.instructure.com/courses/170679/quizzes/599641 5/7 twice the length of the wingspan above the surface. less than the length of the wingspan above the surface. When the wing is at a height equal to its span, the reduction in induced drag is only 1.4%. However, when the wing is at a height equal to one-fourth its span, the reduction in induced drag is 23.5% and when the wing is at a height equal to one-tenth its span, the reduction in induced drag is 47.6%.  Question 15 4 / 4 pts less stable at slow speeds, but more stable at high speeds. less stable at all speeds. less stable at high speeds, but more stable at low speeds. Loading in a tail-heavy condition can reduce the airplane's ability to recover from stalls and spins. Tail-heavy loading also produces very light stick forces at all speeds, making it easy for the pilot to inadvertently overstress the airplane.  Question 16 4 / 4 pts Aircraft power, pitch, bank, and trim. Starting, taxiing, takeoff, and landing. Straight-and-level flight, turns, climbs, and descents. The four flight fundamentals involved in maneuvering an aircraft are: straight-and-level flight, turns, climbs, and descents.  Question 17 4 / 4 pts 4,600 pounds. 2,300 pounds. 3,400 pounds. Referencing FAA Figure 2, use the following steps: 1. Enter the chart at a 60° angle of bank and proceed upward to the curved reference line. From the point of intersection, move to the left side of the chart and read a load factor of 2 Gs. 2. Multiply the aircraft weight by the load factor: 2,300 x 2 = 4,600 lbs Or, working from the table: 2,300 x 2.0 (load factor) = 4,600 lbs  Question 18 4 / 4 pts not spin. require less effort to control. be difficult to stall. Loading an airplane to the most aft CG will cause the airplane to be Select the four flight fundamentals involved in maneuvering an aircraft. (Refer to Figure 2.) If an airplane weighs 2,300 pounds, what approximate weight would the airplane structure be required to support during a 60° banked turn while maintaining altitude? An airplane said to be inherently stable will

3/24/24, 1:22 PM 1.8 Aerodynamics Quiz: ASCI 121 Private Pilot Operations - Mar 2024 - Online https://erau.instructure.com/courses/170679/quizzes/599641 6/7 A stable airplane will tend to return to the original condition of flight if disturbed by a force such as turbulent air. This means that a stable airplane is easy to fly.  Question 19 4 / 4 pts incidence. attack. lift. The angle of attack is the acute angle between the chord line of the wing and the direction of the relative wind.  Question 20 4 / 4 pts remain the same regardless of altitude. decrease as the true airspeed decreases. decrease as the true airspeed increases. An increase in altitude has no effect on the indicated airspeed at which an airplane stalls at altitudes normally used by general aviation aircraft. This means that the same indicated airspeed should be maintained during the landing approach regardless of the elevation or the density altitude at the airport of landing.  Question 21 4 / 4 pts light, quartering tailwind. strong headwind. light, quartering headwind. A tailwind condition can move the vortices of a preceding aircraft forward into the touchdown zone. A light quartering tailwind requires maximum caution. Pilots should be alert to large aircraft upwind from their approach and takeoff flight paths.  Question 22 4 / 4 pts decrease the angle of descent without increasing the airspeed. permit a touchdown at a higher indicated airspeed. increase the angle of descent without increasing the airspeed. Flaps increase drag, allowing the pilot to make steeper approaches without increasing airspeed.  Question 23 4 / 4 pts The angle between the chord line of an airfoil and the relative wind is known as the angle of As altitude increases, the indicated airspeed at which a given airplane stalls in a particular configuration will The wind condition that requires maximum caution when avoiding wake turbulence on landing is a One of the main functions of flaps during approach and landing is to What causes an airplane (except a T-tail) to pitch nosedown when power is reduced and controls are not adjusted?

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3/24/24, 1:22 PM 1.8 Aerodynamics Quiz: ASCI 121 Private Pilot Operations - Mar 2024 - Online https://erau.instructure.com/courses/170679/quizzes/599641 7/7 The CG shifts forward when thrust and drag are reduced. The downwash on the elevators from the propeller slipstream is reduced and elevator effectiveness is reduced. When thrust is reduced to less than weight, lift is also reduced and the wings can no longer support the weight. The location of the center of gravity with respect to the center of lift determines to a great extent the longitudinal stability of an airplane. Center of gravity aft of the center of lift will result in an undesirable pitch-up moment during flight. An airplane with the center of gravity forward of the center of lift will pitch down when power is reduced. This will increase the airspeed and the downward force on the elevators. This increased downward force on the elevators will bring the nose up, providing positive stability. The farther forward the CG is, the more stable the airplane.  Question 24 4 / 4 pts The result of the interference of the surface of the Earth with the airflow patterns about an airplane. The result of the disruption of the airflow patterns about the wings of an airplane to the point where the wings will no longer support the airplane in flight. The result of an alteration in airflow patterns increasing induced drag about the wings of an airplane. Ground effect is the result of the interference of the surface of the Earth with the airflow patterns about an airplane.  Question 25 4 / 4 pts 1,200 pounds. 3,960 pounds. 3,100 pounds. Referencing FAA Figure 2, use the following steps: 1. Enter the chart at a 30° angle of bank and proceed upward to the curved reference line. From the point of intersection, move to the left side of the chart and read an approximate load factor of 1.2 Gs. 2. Multiply the aircraft weight by the load factor: 3,300 x 1.2 = 3,960 lbs Or, working from the table: 3,300 x 1.154 (load factor) = 3,808 lbs Answer C is the closest. Quiz Score: 100 out of 100 What is ground effect? (Refer to Figure 2.) If an airplane weighs 3,300 pounds, what approximate weight would the airplane structure be required to support during a 30° banked turn while maintaining altitude?