- •Textbook Series
- •Contents
- •1 Overview and Definitions
- •Overview
- •General Definitions
- •Glossary
- •List of Symbols
- •Greek Symbols
- •Others
- •Self-assessment Questions
- •Answers
- •2 The Atmosphere
- •Introduction
- •The Physical Properties of Air
- •Static Pressure
- •Temperature
- •Air Density
- •International Standard Atmosphere (ISA)
- •Dynamic Pressure
- •Key Facts
- •Measuring Dynamic Pressure
- •Relationships between Airspeeds
- •Airspeed
- •Errors and Corrections
- •V Speeds
- •Summary
- •Questions
- •Answers
- •3 Basic Aerodynamic Theory
- •The Principle of Continuity
- •Bernoulli’s Theorem
- •Streamlines and the Streamtube
- •Summary
- •Questions
- •Answers
- •4 Subsonic Airflow
- •Aerofoil Terminology
- •Basics about Airflow
- •Two Dimensional Airflow
- •Summary
- •Questions
- •Answers
- •5 Lift
- •Aerodynamic Force Coefficient
- •The Basic Lift Equation
- •Review:
- •The Lift Curve
- •Interpretation of the Lift Curve
- •Density Altitude
- •Aerofoil Section Lift Characteristics
- •Introduction to Drag Characteristics
- •Lift/Drag Ratio
- •Effect of Aircraft Weight on Minimum Flight Speed
- •Condition of the Surface
- •Flight at High Lift Conditions
- •Three Dimensional Airflow
- •Wing Terminology
- •Wing Tip Vortices
- •Wake Turbulence: (Ref: AIC P 072/2010)
- •Ground Effect
- •Conclusion
- •Summary
- •Answers from page 77
- •Answers from page 78
- •Questions
- •Answers
- •6 Drag
- •Introduction
- •Parasite Drag
- •Induced Drag
- •Methods of Reducing Induced Drag
- •Effect of Lift on Parasite Drag
- •Aeroplane Total Drag
- •The Effect of Aircraft Gross Weight on Total Drag
- •The Effect of Altitude on Total Drag
- •The Effect of Configuration on Total Drag
- •Speed Stability
- •Power Required (Introduction)
- •Summary
- •Questions
- •Annex C
- •Answers
- •7 Stalling
- •Introduction
- •Cause of the Stall
- •The Lift Curve
- •Stall Recovery
- •Aircraft Behaviour Close to the Stall
- •Use of Flight Controls Close to the Stall
- •Stall Recognition
- •Stall Speed
- •Stall Warning
- •Artificial Stall Warning Devices
- •Basic Stall Requirements (EASA and FAR)
- •Wing Design Characteristics
- •The Effect of Aerofoil Section
- •The Effect of Wing Planform
- •Key Facts 1
- •Super Stall (Deep Stall)
- •Factors that Affect Stall Speed
- •1g Stall Speed
- •Effect of Weight Change on Stall Speed
- •Composition and Resolution of Forces
- •Using Trigonometry to Resolve Forces
- •Lift Increase in a Level Turn
- •Effect of Load Factor on Stall Speed
- •Effect of High Lift Devices on Stall Speed
- •Effect of CG Position on Stall Speed
- •Effect of Landing Gear on the Stall Speed
- •Effect of Engine Power on Stall Speed
- •Effect of Mach Number (Compressibility) on Stall Speed
- •Effect of Wing Contamination on Stall Speed
- •Warning to the Pilot of Icing-induced Stalls
- •Stabilizer Stall Due to Ice
- •Effect of Heavy Rain on Stall Speed
- •Stall and Recovery Characteristics of Canards
- •Spinning
- •Primary Causes of a Spin
- •Phases of a Spin
- •The Effect of Mass and Balance on Spins
- •Spin Recovery
- •Special Phenomena of Stall
- •High Speed Buffet (Shock Stall)
- •Answers to Questions on Page 173
- •Key Facts 2
- •Questions
- •Key Facts 1 (Completed)
- •Key Facts 2 (Completed)
- •Answers
- •8 High Lift Devices
- •Purpose of High Lift Devices
- •Take-off and Landing Speeds
- •Augmentation
- •Flaps
- •Trailing Edge Flaps
- •Plain Flap
- •Split Flap
- •Slotted and Multiple Slotted Flaps
- •The Fowler Flap
- •Comparison of Trailing Edge Flaps
- •and Stalling Angle
- •Drag
- •Lift / Drag Ratio
- •Pitching Moment
- •Centre of Pressure Movement
- •Change of Downwash
- •Overall Pitch Change
- •Aircraft Attitude with Flaps Lowered
- •Leading Edge High Lift Devices
- •Leading Edge Flaps
- •Effect of Leading Edge Flaps on Lift
- •Leading Edge Slots
- •Leading Edge Slat
- •Automatic Slots
- •Disadvantages of the Slot
- •Drag and Pitching Moment of Leading Edge Devices
- •Trailing Edge Plus Leading Edge Devices
- •Sequence of Operation
- •Asymmetry of High Lift Devices
- •Flap Load Relief System
- •Choice of Flap Setting for Take-off, Climb and Landing
- •Management of High Lift Devices
- •Flap Extension Prior to Landing
- •Questions
- •Annexes
- •Answers
- •9 Airframe Contamination
- •Introduction
- •Types of Contamination
- •Effect of Frost and Ice on the Aircraft
- •Effect on Instruments
- •Effect on Controls
- •Water Contamination
- •Airframe Aging
- •Questions
- •Answers
- •10 Stability and Control
- •Introduction
- •Static Stability
- •Aeroplane Reference Axes
- •Static Longitudinal Stability
- •Neutral Point
- •Static Margin
- •Trim and Controllability
- •Key Facts 1
- •Graphic Presentation of Static Longitudinal Stability
- •Contribution of the Component Surfaces
- •Power-off Stability
- •Effect of CG Position
- •Power Effects
- •High Lift Devices
- •Control Force Stability
- •Manoeuvre Stability
- •Stick Force Per ‘g’
- •Tailoring Control Forces
- •Longitudinal Control
- •Manoeuvring Control Requirement
- •Take-off Control Requirement
- •Landing Control Requirement
- •Dynamic Stability
- •Longitudinal Dynamic Stability
- •Long Period Oscillation (Phugoid)
- •Short Period Oscillation
- •Directional Stability and Control
- •Sideslip Angle
- •Static Directional Stability
- •Contribution of the Aeroplane Components.
- •Lateral Stability and Control
- •Static Lateral Stability
- •Contribution of the Aeroplane Components
- •Lateral Dynamic Effects
- •Spiral Divergence
- •Dutch Roll
- •Pilot Induced Oscillation (PIO)
- •High Mach Numbers
- •Mach Trim
- •Key Facts 2
- •Summary
- •Questions
- •Key Facts 1 (Completed)
- •Key Facts 2 (Completed)
- •Answers
- •11 Controls
- •Introduction
- •Hinge Moments
- •Control Balancing
- •Mass Balance
- •Longitudinal Control
- •Lateral Control
- •Speed Brakes
- •Directional Control
- •Secondary Effects of Controls
- •Trimming
- •Questions
- •Answers
- •12 Flight Mechanics
- •Introduction
- •Straight Horizontal Steady Flight
- •Tailplane and Elevator
- •Balance of Forces
- •Straight Steady Climb
- •Climb Angle
- •Effect of Weight, Altitude and Temperature.
- •Power-on Descent
- •Emergency Descent
- •Glide
- •Rate of Descent in the Glide
- •Turning
- •Flight with Asymmetric Thrust
- •Summary of Minimum Control Speeds
- •Questions
- •Answers
- •13 High Speed Flight
- •Introduction
- •Speed of Sound
- •Mach Number
- •Effect on Mach Number of Climbing at a Constant IAS
- •Variation of TAS with Altitude at a Constant Mach Number
- •Influence of Temperature on Mach Number at a Constant Flight Level and IAS
- •Subdivisions of Aerodynamic Flow
- •Propagation of Pressure Waves
- •Normal Shock Waves
- •Critical Mach Number
- •Pressure Distribution at Transonic Mach Numbers
- •Properties of a Normal Shock Wave
- •Oblique Shock Waves
- •Effects of Shock Wave Formation
- •Buffet
- •Factors Which Affect the Buffet Boundaries
- •The Buffet Margin
- •Use of the Buffet Onset Chart
- •Delaying or Reducing the Effects of Compressibility
- •Aerodynamic Heating
- •Mach Angle
- •Mach Cone
- •Area (Zone) of Influence
- •Bow Wave
- •Expansion Waves
- •Sonic Bang
- •Methods of Improving Control at Transonic Speeds
- •Questions
- •Answers
- •14 Limitations
- •Operating Limit Speeds
- •Loads and Safety Factors
- •Loads on the Structure
- •Load Factor
- •Boundary
- •Design Manoeuvring Speed, V
- •Effect of Altitude on V
- •Effect of Aircraft Weight on V
- •Design Cruising Speed V
- •Design Dive Speed V
- •Negative Load Factors
- •The Negative Stall
- •Manoeuvre Boundaries
- •Operational Speed Limits
- •Gust Loads
- •Effect of a Vertical Gust on the Load Factor
- •Effect of the Gust on Stalling
- •Operational Rough-air Speed (V
- •Landing Gear Speed Limitations
- •Flap Speed Limit
- •Aeroelasticity (Aeroelastic Coupling)
- •Flutter
- •Control Surface Flutter
- •Aileron Reversal
- •Questions
- •Answers
- •15 Windshear
- •Introduction (Ref: AIC 84/2008)
- •Microburst
- •Windshear Encounter during Approach
- •Effects of Windshear
- •“Typical” Recovery from Windshear
- •Windshear Reporting
- •Visual Clues
- •Conclusions
- •Questions
- •Answers
- •16 Propellers
- •Introduction
- •Definitions
- •Aerodynamic Forces on the Propeller
- •Thrust
- •Centrifugal Twisting Moment (CTM)
- •Propeller Efficiency
- •Variable Pitch Propellers
- •Power Absorption
- •Moments and Forces Generated by a Propeller
- •Effect of Atmospheric Conditions
- •Questions
- •Answers
- •17 Revision Questions
- •Questions
- •Answers
- •Explanations to Specimen Questions
- •Specimen Examination Paper
- •Answers to Specimen Exam Paper
- •Explanations to Specimen Exam Paper
- •18 Index
Windshear 15
Windshear Encounter during Approach
The power setting and vertical velocity required to maintain the glide slope should be closely monitored. If any windshear is encountered, it may be difficult to stay on the glide path at normal power and descent rates. If there is ever any doubt that you can regain a reasonable rate of descent, and land without abnormal manoeuvres, you should apply full power and go-around or make a missed approach.
Windshear can vary enormously in its impact and effect. Clearly some shears will be more severe and consequently more dangerous than others.
When countering the effects of windshear, it is best to assume ‘worse case’. It is impossible to predict at the first stages of a windshear encounter how severe it will be, and it is good advice to suggest that recovery action should anticipate the worst.
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WINDSHEAR |
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Headwind |
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Calm or Tailwind |
Tailwind |
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Calm or Headwind |
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INDICATIONS |
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Indicated Airspeed |
Decrease |
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Pitch Attitude |
Decrease |
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Increase |
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Windshear |
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ACTIONS |
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Down to Glideslope |
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To Stay on Glide Path |
Increase Rate of Descent |
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Figure 15.2 Indications & recovery actions for windshear encounter during approach
Referring to Figure 15.2, this table gives guidance should you encounter windshear during a stabilized landing approach. Approaches should never be attempted into known windshear conditions.
491
15 Windshear
Effects of Windshear
Windshear 15
The relationship of an aeroplane in a moving air mass to its two reference points must be fully understood. One reference is the air mass itself and the other is the ground.
On passing through a shear line, the change of airspeed will be sudden, but the inertia of the aircraft will at first keep it at its original ground speed. The wind is a form of energy and when it shears, an equivalent amount of energy is lost or gained.
•A rapid increase in headwind (or loss of tailwind) are both ‘energy gains’, and will temporarily improve performance, Figure 15.3.
•Downdraughts or a sudden drop of headwind (or increase in tailwind) are the main danger at low altitude because they give an ‘energy loss’, Figure 15.4 and 15.5.
'ENERGY GAIN' - Rapid increase in headwind.
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10 kt |
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Vertical Speed: |
200 ft/min R.O.C. |
Vertical Speed: |
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Ground Speed: |
130 kt |
Ground Speed: |
130 kt |
IAS: |
190 kt |
IAS: |
140 kt |
GLIDE SLOPE
SHEAR
LINE
Figure 15.3 “Energy gain” due to increase in headwind
492
Windshear 15
'ENERGY LOSS' - Effect of downdraught.
10 kt
Vertical Speed: |
1500 ft/min R.O.D. |
Vertical Speed: |
700 ft/min R.O.D. |
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Ground Speed: |
130 kt |
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Ground Speed: |
130 kt |
GLIDE SLOPE |
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130 kt |
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SHEAR |
LINE |
Figure 15.4 “Energy loss” due to downdraught
'ENERGY LOSS' - Loss of headwind.
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Vertical Speed: |
1000 ft/min R.O.D. |
Vertical Speed: |
700 ft/min R.O.D. |
Ground Speed: |
130 kt |
Ground Speed: |
130 kt |
IAS: |
110 kt |
IAS: |
140 kt |
GLIDE SLOPE
20 kt
SHEAR |
LINE |
Windshear 15
Figure 15.5 “Energy loss” due to loss of headwind
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15 Windshear
“Typical” Recovery from Windshear
The combination of increasing headwind, followed by downdraught, followed by increasing tailwind should be considered, as this is the sequence which might be encountered in a microburst on the approach, or following take-off.
• The presence of thunderstorms should be known and obvious, so the increase in speed caused by the rising headwind should be seen as the forerunner of a down-burst or microburst; any hope of a stabilized approach should be abandoned and a missed approach carried out
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The initial rise in airspeed and rise above the approach path (balloon) should be seen |
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as a bonus and capitalized on. Without hesitation, increase to go-around power, being |
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prepared to go to maximum power if necessary, select a pitch angle consistent with a |
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missed approach, typically about 15°, and hold it against turbulence and buffeting. |
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The next phase may well see the initial advantages of increased airspeed and rate of climb |
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being rapidly eroded. The downdraught now strikes, airspeed may be lost and the aircraft |
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may start to descend, despite the high power and pitch angle. It will be impossible to |
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gauge the true angle of attack, so there is a possibility that the stick shaker (if fitted) may be |
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triggered; only then should the attempt to hold the pitch angle normally be relaxed. |
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• the point at which a downdraught begins to change to increasing tailwind may well be the |
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most critical period. The rate of descent may lessen, but the airspeed may still continue to |
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fall; the height loss may have cut seriously into ground obstacle clearance margins. Given |
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that maximum thrust is already applied, as an extreme measure if the risk of striking the |
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Windshear |
ground or an obstacle still exists, it may be necessary to increase the pitch angle further |
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the pitch control to try and hold this higher pitch angle, until the situation eases with the |
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and deliberately raise the nose until stick shaker is felt, then decrease back-pressure on |
aircraft beginning to escape from the effects of the microburst.
When there is an indefinite risk of shear, it may be possible to use a longer runway, or one that points away from an area of potential threat. It may also be an option to rotate at a slightly higher speed, provided this does not cause undue tyre stress or any handling problems. The high power setting and high pitch angle after rotate already put the aircraft into a good configuration should a microburst then be encountered. The aircraft is, however, very low, there is little safety margin and the ride can be rough. If there is still extra power available, it should be used without hesitation. Ignore noise abatement procedures and maintain the high pitch angle, watching out for stick shaker indications as a signal to decrease backpressure on the pitch control.
In both approach and take-off cases, vital actions are:
•Use the maximum power available as soon as possible.
•Adopt a pitch angle of around 15° and try and hold that attitude. Do not chase airspeed.
•Be guided by stick shaker indications when holding or increasing pitch attitude, easing the back-pressure as required to attain and hold a slightly lower attitude.
494