AVIA 305: AIRCRAFT
PERFORMANCE; QUESTIONS AND
ANSWERS WITH RATIONALES/
GRADED A+/2026 UPDATE
/100%CORRECT
SECTION I: FUNDAMENTALS OF AERODYNAMICS & ATMOSPHERE
*(Questions 1-12)*
1. What is the definition of "Absolute Ceiling"?
a) The altitude where the maximum rate of climb is 100 fpm.
b) The altitude where the maximum rate of climb is 500 fpm.
c) The altitude where the maximum rate of climb is zero.
d) The altitude where the maximum rate of climb is zero.
Rationale: The absolute ceiling is the altitude at which the aircraft can no longer
climb (rate of climb is zero). Service ceiling is where ROC is 100 fpm (for piston)
or 500 fpm (for jet).
2. How does a decrease in ambient temperature affect pressure altitude and
density altitude, assuming actual altitude remains constant?
a) Pressure altitude increases; Density altitude increases.
b) Pressure altitude decreases; Density altitude increases.
c) Pressure altitude remains constant; Density altitude increases.
d) Pressure altitude remains constant; Density altitude decreases.
Rationale: Pressure altitude is based on barometric pressure, not temperature.
Density altitude is pressure altitude corrected for non-standard temperature. Colder
air is denser, thus lower density altitude.
3. As an aircraft accelerates through the transonic region (Mach 0.7 to 1.2),
the center of pressure (CP) typically shifts:
a) Forward, causing a nose-down tendency.
,b) Aft, causing a nose-down tendency.
c) Forward, causing a nose-up tendency.
d) Aft, causing a nose-up tendency.
Rationale: As shock waves form, the CP moves aft, increasing the pitching
moment and causing "Mach tuck" (nose-down tendency).
4. For a turbojet engine, thrust output is approximately proportional to:
a) RPM squared.
b) The difference between exit velocity and free stream velocity.
c) The density of the fuel.
d) Propeller efficiency.
Rationale: Based on Newton’s second law (F = ṁ * (V_exit – V_inlet)). Turbojet
thrust is dependent on the momentum change of the air, not simply RPM.
5. Which of the following best describes "Total Drag" on a typical fixed-wing
aircraft?
a) The sum of induced drag and thrust drag.
b) The sum of induced drag and parasite drag.
c) The sum of profile drag and induced drag minus lift.
d) The sum of skin friction and induced drag only.
Rationale: Total drag in steady-state flight is the combination of induced drag
(byproduct of lift) and parasite drag (skin friction, form, interference).
6. At sea level on a standard day, what is the pressure altitude if the altimeter
is set to 29.92 inHg?
a) 500 ft
b) 1,000 ft
c) 0 ft
d) Variable depending on temperature
Rationale: Pressure altitude is the altitude in the standard atmosphere
corresponding to the current pressure. When the altimeter is set to 29.92, it reads
pressure altitude. At sea level standard day, it reads zero.
7. What effect does a high density altitude have on takeoff performance?
a) Shorter takeoff roll and higher rate of climb.
b) Longer takeoff roll and reduced rate of climb.
, c) Shorter takeoff roll but reduced rate of climb.
d) No effect on takeoff roll but higher true airspeed.
Rationale: High density altitude (hot, high, humid) means less dense air. The
engine produces less power, and the wings produce less lift, requiring a higher true
airspeed (and thus longer ground roll) to become airborne.
8. The "Lift Equation" (L = CL * ½ρV² * S) demonstrates that to maintain
level flight at a higher altitude (lower ρ), a pilot must:
a) Decrease angle of attack.
b) Increase true airspeed.
c) Decrease true airspeed.
d) Reduce gross weight.
Rationale: To maintain lift equal to weight (L=W), if ρ decreases, the pilot must
increase TAS or increase CL (angle of attack) to compensate.
9. Which force opposes the motion of an aircraft through the air and acts
parallel to the relative wind?
a) Lift
b) Weight
c) Drag
d) Thrust
Rationale: Drag is the aerodynamic force that opposes the aircraft’s motion
through the air, acting parallel to the relative wind.
10. In the context of aircraft performance, "Viscosity" primarily affects:
a) Induced drag.
b) Parasite drag (skin friction).
c) Lift coefficient.
d) Thrust specific fuel consumption.
Rationale: Viscosity is the property of a fluid (air) that resists shear. It directly
influences skin friction drag, a component of parasite drag.
11. When flying in the Northern Hemisphere, what effect does the Coriolis
Force have on large-scale weather patterns that impact flight planning?
a) It causes air to flow directly from high to low pressure.
b) It causes air to deflect to the right, creating cyclonic rotation.
PERFORMANCE; QUESTIONS AND
ANSWERS WITH RATIONALES/
GRADED A+/2026 UPDATE
/100%CORRECT
SECTION I: FUNDAMENTALS OF AERODYNAMICS & ATMOSPHERE
*(Questions 1-12)*
1. What is the definition of "Absolute Ceiling"?
a) The altitude where the maximum rate of climb is 100 fpm.
b) The altitude where the maximum rate of climb is 500 fpm.
c) The altitude where the maximum rate of climb is zero.
d) The altitude where the maximum rate of climb is zero.
Rationale: The absolute ceiling is the altitude at which the aircraft can no longer
climb (rate of climb is zero). Service ceiling is where ROC is 100 fpm (for piston)
or 500 fpm (for jet).
2. How does a decrease in ambient temperature affect pressure altitude and
density altitude, assuming actual altitude remains constant?
a) Pressure altitude increases; Density altitude increases.
b) Pressure altitude decreases; Density altitude increases.
c) Pressure altitude remains constant; Density altitude increases.
d) Pressure altitude remains constant; Density altitude decreases.
Rationale: Pressure altitude is based on barometric pressure, not temperature.
Density altitude is pressure altitude corrected for non-standard temperature. Colder
air is denser, thus lower density altitude.
3. As an aircraft accelerates through the transonic region (Mach 0.7 to 1.2),
the center of pressure (CP) typically shifts:
a) Forward, causing a nose-down tendency.
,b) Aft, causing a nose-down tendency.
c) Forward, causing a nose-up tendency.
d) Aft, causing a nose-up tendency.
Rationale: As shock waves form, the CP moves aft, increasing the pitching
moment and causing "Mach tuck" (nose-down tendency).
4. For a turbojet engine, thrust output is approximately proportional to:
a) RPM squared.
b) The difference between exit velocity and free stream velocity.
c) The density of the fuel.
d) Propeller efficiency.
Rationale: Based on Newton’s second law (F = ṁ * (V_exit – V_inlet)). Turbojet
thrust is dependent on the momentum change of the air, not simply RPM.
5. Which of the following best describes "Total Drag" on a typical fixed-wing
aircraft?
a) The sum of induced drag and thrust drag.
b) The sum of induced drag and parasite drag.
c) The sum of profile drag and induced drag minus lift.
d) The sum of skin friction and induced drag only.
Rationale: Total drag in steady-state flight is the combination of induced drag
(byproduct of lift) and parasite drag (skin friction, form, interference).
6. At sea level on a standard day, what is the pressure altitude if the altimeter
is set to 29.92 inHg?
a) 500 ft
b) 1,000 ft
c) 0 ft
d) Variable depending on temperature
Rationale: Pressure altitude is the altitude in the standard atmosphere
corresponding to the current pressure. When the altimeter is set to 29.92, it reads
pressure altitude. At sea level standard day, it reads zero.
7. What effect does a high density altitude have on takeoff performance?
a) Shorter takeoff roll and higher rate of climb.
b) Longer takeoff roll and reduced rate of climb.
, c) Shorter takeoff roll but reduced rate of climb.
d) No effect on takeoff roll but higher true airspeed.
Rationale: High density altitude (hot, high, humid) means less dense air. The
engine produces less power, and the wings produce less lift, requiring a higher true
airspeed (and thus longer ground roll) to become airborne.
8. The "Lift Equation" (L = CL * ½ρV² * S) demonstrates that to maintain
level flight at a higher altitude (lower ρ), a pilot must:
a) Decrease angle of attack.
b) Increase true airspeed.
c) Decrease true airspeed.
d) Reduce gross weight.
Rationale: To maintain lift equal to weight (L=W), if ρ decreases, the pilot must
increase TAS or increase CL (angle of attack) to compensate.
9. Which force opposes the motion of an aircraft through the air and acts
parallel to the relative wind?
a) Lift
b) Weight
c) Drag
d) Thrust
Rationale: Drag is the aerodynamic force that opposes the aircraft’s motion
through the air, acting parallel to the relative wind.
10. In the context of aircraft performance, "Viscosity" primarily affects:
a) Induced drag.
b) Parasite drag (skin friction).
c) Lift coefficient.
d) Thrust specific fuel consumption.
Rationale: Viscosity is the property of a fluid (air) that resists shear. It directly
influences skin friction drag, a component of parasite drag.
11. When flying in the Northern Hemisphere, what effect does the Coriolis
Force have on large-scale weather patterns that impact flight planning?
a) It causes air to flow directly from high to low pressure.
b) It causes air to deflect to the right, creating cyclonic rotation.
