Embedded Files
Topic: Aircraft Climb Performance
Topic: Aircraft Climb Performance
Sub Topics:
Sub Topics:
Rate of Climb
Maximum Climb Angle
Maximum Rate of Climb
Time to Climb
Effect of Wind on Climb Performance
Service and Absolute Ceiling
Objective : What I want you to learn?
Objective : What I want you to learn?
Derive the mathematical expression for calculating the steady rate of climb, maximum climb angle, maximum rate of climb and time to climb of an aircraft.
Evaluate and Analyze the parameters that affect the climb performance of an aircraft such as Velocity, Weight, Aspect Ratio and External factors like altitude and wind
Rationale : Why this is useful to you?
Rationale : Why this is useful to you?
The mathematical expressions that you derive are useful for evaluating the climb performance of a given aircraft under the atmospheric conditions.
By evaluating and analyzing the parameters that affect the climb performance, it is helpful in engine selection in the aircraft design process.
Learning Outcomes : What I want you to do after completing this topic?
Learning Outcomes : What I want you to do after completing this topic?
Derive the mathematical expression for calculating the steady rate of climb, maximum climb angle, maximum rate of climb and time to climb of an aircraft.
Calculate the maximum climb angle, maximum rate of climb and time to climb for a given aircraft under given atmospheric conditions.
Comment on the parameters and factors that affect the climb performance by analyzing them.
Equations of Motion for Climbing Flight - Rate of Climb (ROC)
Equations of Motion for Climbing Flight - Rate of Climb (ROC)
Maximum Climb Angle
Maximum Climb Angle
Maximum Rate of Climb
Maximum Rate of Climb
Time to Climb
Time to Climb
Effect of Altitude and Wind on Climb Performance
Effect of Altitude and Wind on Climb Performance
Service Ceiling and Absolute Ceiling
Service Ceiling and Absolute Ceiling
Summary
Summary
Tutorial Problems
Tutorial Problems
Practice Problems
Practice Problems
An airplane weighing 180,000 N has a wing area of 45 m^2 and drag polar given by CD = 0.017 + 0.05 CL^2 .
1. Obtain the thrust required and power required for a rate of climb of 2,000 m/min at a speed of 540 kmph at 3 km altitude.
2. Calculate the angle of climb and the rate of climb at a flight speed of 400 kmph at sea level, taking the thrust available as 45,000 N.
GATE Questions (2007 - 2019)
GATE Questions (2007 - 2019)
Page updated
Report abuse