Avia 305 Study guides, Class notes & Summaries

AVIA 305 TEST 1 2021/2022 Correct answers are hidden. Score for this quiz: 65 out of 75 Submitted Jan 21 at 7:33pm This attempt took 53 minutes. IncorrectQuestion 1 0 / 2.5 pts A slotted flap is an example of a(n) (Ref Figure 1) Camber changer Energy adder Area changer A & B Question 2 2.5 / 2.5 pts

AVIA 305 Quiz: Maneuvering Performance Score for this quiz: 72.5 out of 75 Fall 2023 Score for this quiz: 72.5 out of 75 During a right crosswind landing in a tricycle gear airplane, a coordinated touchdown on the wheel first will mitigate side loading and prevent ground looping the aircraft. right left nosewheel tailwheel During a setup to a power-on stall in a single-engine propeller airplane, as IAS decreases additional input will be required to maintain coordinated flight. ri...

AVIA 305 QUIZ Aircraft Performance • Question 1 The power-required curves for an increase in altitude show that the • Question 2 The equation Ta=Q(V2-V1) shows that • Question 3 The lowest point on the Pr curve is (L/D)MAX • Question 4 A gas turbine engine that uses most of its power to drive a propeller. • Question 5 (Reference Figure 7.2) Using Figure 7.2, find the velocity for best range for the airplane at 12,000 lbs. • Question 6 An engine that utilizes compressed air, via a com...

AVIA 305 Review Test Submission: Test 1 Attempt Score 57.5 out of 75 points • • Question 1 An airplane is operating from an airfield that has a barometric pressure of 28.86 in. Hg and a runway temperature of 20C. Calculate (or find in Table 2.1) the Temperature Ratio: • Question 2 The corrections that must be made to indicated airspeed (IAS) to obtain calibrated airspeed (CAS) are: • Question 3 A large Reynolds number (greater than 10 million) indicates • Question 4 An airplane is oper...

LU AVIA 305 Quiz 4 • Question 1 In Subsonic flight the air is considered to be • Question 2 2.5 out of 2.5 points A Normal shock wave will have what effect on velocity and Mach number? • Question 3 2.5 out of 2.5 points Aircraft speeds where the airflow around the aircraft ranges between Mach 0.7 and Mach 1.3 is • Question 4 2.5 out of 2.5 points A "stable" aircraft wing design is one where the

New AVIA 305 QUIZ Aircraft Performance • Question 1 The power-required curves for an increase in altitude show that the • Question 2 The equation Ta=Q(V2-V1) shows that

AVIA 305 Test 3 • Question 1 Which statement is true with respect to Lift Coefficient (CL) and the Effect of Sweepback on Coefficient of Lift - Angle of Attack (AOA) curves. • Question 2 For a safe takeoff, the Critical Field Length must be no greater than the runway available • Question 3 An...

An airplane is towing a glider to altitude. The tow rope is 20° below the horizontal and has a tension force of 300 lb exerted on it by the airplane. Find the horizontal drag of the glider and the amount of lift that the rope is providing to the glider. Sin 20° = 0.342; cos 20 °= 0.940.Drag: Cos 20° = D/T (Rearrange) D = Cos 20° X Tension D = 0.940 X 300lbs D = 282lbs Lift: Sin 20° = L/T (Rearrange) Lift = Sin 20° X Tension Lift = 0.342 X 300 lbs

The difference between the CL curves for straight-wing aircraft is that a) the swept wing aircraft has a lower value of CL (max) b) the straight wing aircraft does not fly at as high an AOA for CL (max) c) the swept wing aircraft does not have an abrupt loss of lift at CL (max) d) all of the above d) all of the above Low speed stall will start at the wing's trailing edge a) where C1/C2 is a minimum b) where C1/C2 is a maximum c) at the root for a swept wing d) at the wingtip for a st...