This document discusses aircraft take-off and landing performance. It provides equations to calculate take-off ground roll distance and total take-off distance based on factors like thrust, weight, wing area, and lift coefficient. The document also discusses regulations for landing performance and provides an empirical equation to calculate total landing distance. It concludes by providing recommended lift coefficient ranges for take-off and landing for fighter and transport aircraft design.
This document discusses airplane upset recovery training at high altitudes. It was created by an industry working group formed at the FAA's request to address unintentional slowdowns and recoveries in the high altitude environment. The goal is to educate pilots on operating airplanes and preventing upsets in this environment. The training aid covers high altitude aerodynamics principles, flight techniques, considerations, and upset recovery training. Key topics include the reduced operational envelope at high altitudes requiring smooth control inputs, avoiding speeds lower than L/D max, understanding concepts like optimum and maximum altitudes, and buffet margins.
Airspeeds | Q & A | Question Analysis | Flight Mechanics | GATE AerospaceAge of Aerospace
Question Analysis, Book Reference, Important Concepts, Formulae and topic wise Solutions for the topic "Airspeeds" are time-stamped below. Access the study materials, presentation, links to previous and next lectures and further information in the description section.
This document discusses approach and landing performance requirements. It covers topics like approach definition, maximum and minimum speeds, landing weight limitations, climb requirements, landing distances, and factors affecting landing distance. Specifically, it defines speeds like VREF (reference landing approach speed) and VAPP (actual landing speed). It also discusses requirements for landing and approach climb gradients, and how to calculate landing distance required versus landing distance available on the runway.
This document provides an overview of the engines on the Airbus A320 series aircraft. It describes the key components and systems, including the IAE V2500 high-bypass turbofan engines, Full Authority Digital Engine Control (FADEC), fuel system, and ignition system. It explains that the FADEC controls and monitors engine operation using EPR or N1 modes. It also discusses engine starts, idle settings, and protections provided during automatic starts on the ground.
1) Climb performance analysis considers factors like thrust, drag, lift, weight and airspeed that determine an aircraft's rate of climb and optimal climb speeds. Maximum angle and rate of climb speeds (Vx and Vy) are evaluated.
2) Factors like pressure altitude, temperature, and weight affect an aircraft's climb capability and rate of climb. Ceilings like service ceiling and design ceiling also limit maximum altitude.
3) For long flights, step climbs are used where the aircraft periodically climbs to higher altitudes to stay close to its optimal cruise altitude as weight decreases from fuel burn.
The document discusses speeds that are important for takeoff performance of JAR 25 aircraft. It defines key speeds such as stall speed, minimum control speeds on the ground and in the air, engine failure speed, minimum unstick speed, lift-off speed, maximum tire speed, and maximum brake energy absorption speed. It also discusses operative speeds used for takeoff including decision speed (V1), rotation speed (VR), and takeoff safety speed (V2). Factors that can affect takeoff performance and speeds are also summarized such as flap setting, runway slope, wind, density altitude, aircraft systems, and runway contamination.
This document discusses various aspects of cruise flight performance and procedures for twin-engine commercial aircraft. It covers topics such as economic Mach number, constant Mach number cruise, maximum endurance, buffet onset, and drift-down procedures for a single engine failure during cruise. Drift-down requires descending to an altitude where the aircraft can maintain level flight on the remaining engines, meeting gradient and obstacle clearance requirements along the drift-down path.
This document discusses aircraft take-off and landing performance. It provides equations to calculate take-off ground roll distance and total take-off distance based on factors like thrust, weight, wing area, and lift coefficient. The document also discusses regulations for landing performance and provides an empirical equation to calculate total landing distance. It concludes by providing recommended lift coefficient ranges for take-off and landing for fighter and transport aircraft design.
This document discusses airplane upset recovery training at high altitudes. It was created by an industry working group formed at the FAA's request to address unintentional slowdowns and recoveries in the high altitude environment. The goal is to educate pilots on operating airplanes and preventing upsets in this environment. The training aid covers high altitude aerodynamics principles, flight techniques, considerations, and upset recovery training. Key topics include the reduced operational envelope at high altitudes requiring smooth control inputs, avoiding speeds lower than L/D max, understanding concepts like optimum and maximum altitudes, and buffet margins.
Airspeeds | Q & A | Question Analysis | Flight Mechanics | GATE AerospaceAge of Aerospace
Question Analysis, Book Reference, Important Concepts, Formulae and topic wise Solutions for the topic "Airspeeds" are time-stamped below. Access the study materials, presentation, links to previous and next lectures and further information in the description section.
This document discusses approach and landing performance requirements. It covers topics like approach definition, maximum and minimum speeds, landing weight limitations, climb requirements, landing distances, and factors affecting landing distance. Specifically, it defines speeds like VREF (reference landing approach speed) and VAPP (actual landing speed). It also discusses requirements for landing and approach climb gradients, and how to calculate landing distance required versus landing distance available on the runway.
This document provides an overview of the engines on the Airbus A320 series aircraft. It describes the key components and systems, including the IAE V2500 high-bypass turbofan engines, Full Authority Digital Engine Control (FADEC), fuel system, and ignition system. It explains that the FADEC controls and monitors engine operation using EPR or N1 modes. It also discusses engine starts, idle settings, and protections provided during automatic starts on the ground.
1) Climb performance analysis considers factors like thrust, drag, lift, weight and airspeed that determine an aircraft's rate of climb and optimal climb speeds. Maximum angle and rate of climb speeds (Vx and Vy) are evaluated.
2) Factors like pressure altitude, temperature, and weight affect an aircraft's climb capability and rate of climb. Ceilings like service ceiling and design ceiling also limit maximum altitude.
3) For long flights, step climbs are used where the aircraft periodically climbs to higher altitudes to stay close to its optimal cruise altitude as weight decreases from fuel burn.
The document discusses speeds that are important for takeoff performance of JAR 25 aircraft. It defines key speeds such as stall speed, minimum control speeds on the ground and in the air, engine failure speed, minimum unstick speed, lift-off speed, maximum tire speed, and maximum brake energy absorption speed. It also discusses operative speeds used for takeoff including decision speed (V1), rotation speed (VR), and takeoff safety speed (V2). Factors that can affect takeoff performance and speeds are also summarized such as flap setting, runway slope, wind, density altitude, aircraft systems, and runway contamination.
This document discusses various aspects of cruise flight performance and procedures for twin-engine commercial aircraft. It covers topics such as economic Mach number, constant Mach number cruise, maximum endurance, buffet onset, and drift-down procedures for a single engine failure during cruise. Drift-down requires descending to an altitude where the aircraft can maintain level flight on the remaining engines, meeting gradient and obstacle clearance requirements along the drift-down path.
This document discusses aircraft flight control systems. It describes three main categories of flight controls: primary, secondary, and auxiliary.
Primary flight controls include elevators, ailerons, and the rudder. Elevators control pitch, ailerons control roll, and the rudder controls yaw. Secondary flight controls include trim tabs which help balance aircraft control forces. Auxiliary controls include flaps and other high lift devices which allow aircraft to fly at slower speeds. The document provides details on how each of these various control surfaces and systems function.
Takeoff and Landing | Flight Mechanics | GATE AerospaceAge of Aerospace
This document provides an overview of the topics covered in a presentation on flight mechanics, takeoff, and landing. The core topics include basics of atmosphere, aircraft classification, airplane configuration, flight instruments, aerodynamic forces, and airplane performance including takeoff, landing, climb, descent, stability, and equations of motion. The presentation will focus on takeoff and landing performance, outlining the different segments of ground roll for takeoff and approach/flare/ground roll distances for landing, as well as factors that influence accelerated performance like drag, minimum control speeds, and decision speeds. References for further information are provided.
This chapter provides an overview of aircraft structure and components. It defines key terms like fuselage, wings, empennage, landing gear, and powerplant. It describes basic aerodynamic concepts like thrust, lift, weight, and drag. It explains how control surfaces like ailerons, elevators, and rudders control the aircraft's pitch, roll, and yaw. It briefly discusses different types of aircraft construction materials and methods.
The document provides training material on landing gear for the B727-200 aircraft. It describes the landing gear components and systems, including the main and nose gears, retraction/extension mechanisms, safety sensors, and electrical/electronic modules. It contains detailed sections on the description, operation, and maintenance of the landing gear and related systems. The training material is for student use only and cannot be distributed without permission.
This document defines abbreviations commonly used in airway manuals to provide concise descriptions of aviation terms. It includes over 200 abbreviations ranging from A/A (Air to Air) to Z (Magnetic Course measured from a VOR station). The abbreviations cover a wide variety of aviation topics including navigation aids, airspace designations, airport identifiers, and meteorological terms.
Ground handling services include all the services an aircraft needs while on the ground at an airport. These services include passenger handling at check-in and arrival, ramp services like aircraft and baggage handling, de-icing, and towing, load control and flight operations support before and after flights, cargo and mail warehouse services, security services throughout travel, and various support services required for successful aircraft handling. It is important to hire an experienced ground handling company, such as Transworld Aviation in Zanzibar, to ensure quality airport services.
The Airport Handling Manual 39th Edition includes several key changes and updates:
- Chapters 2 and 6 were significantly revised or sections were removed and consolidated in other manuals.
- Chapters 3, 4, 5, 7, 8, and 9 saw updates to procedures and guidelines around cargo handling, aircraft loading, load planning, aircraft operations, ground handling agreements, and ground support equipment to improve safety, efficiency, and standardization.
- Specific additions included new guidelines for safety performance indicators, occupational health and safety programs, cargo key performance indicators, and the use of pooled ground support equipment.
This document provides guidance on standards and recommended practices for securing civil aviation against unlawful interference. It covers definitions, general principles, organization of national aviation security programs, and components of effective security systems. Key areas discussed include designation of appropriate security authorities, national security legislation and regulations, threat assessment, security training, airport security programs, contingency planning, and international cooperation. The document aims to establish comprehensive security measures to safeguard international air transport.
The document discusses aircraft flight control systems. It describes the primary flight controls which include the elevator, aileron, and rudder control systems. The elevator controls pitch, the ailerons control roll, and the rudder controls yaw. Secondary flight controls include trim tabs that help balance aircraft control forces. Auxiliary controls include flaps, slats, and spoilers which help with lift during takeoff and landing. The document also provides an overview of autopilot systems, how they receive input from sensors and gyros, and how they output movements to flight control surfaces like ailerons and elevators to guide the aircraft without pilot assistance.
The document summarizes the basic control systems of an aircraft, including primary, secondary, and auxiliary flight controls. Primary controls include elevators, ailerons, and rudders which control pitch, roll, and yaw respectively. Secondary controls include trim tabs which help balance aircraft forces. Auxiliary controls include flaps, spoilers, and slats which provide additional lift, especially at lower speeds. The document describes the purpose and function of each control surface.
Alaska Airlines Airbus Study Presentation 2ShawnSmith231
The document provides information about various aircraft systems. It includes 186 slides with details about the Air Data and Inertial Reference System, ADIRS alignment procedures, emergency electrical configurations, oxygen systems, and engine fire detection and extinguishing. Key points covered are the three ADIRUs that supply data to flight instruments, procedures for ADIRS alignment, what is powered during RAT and battery power, and the components involved in detecting and extinguishing an engine fire.
The Instrument Landing System (ILS) uses radio beams to guide aircraft during low visibility approaches and landings. ILS consists of ground-based transmitters that provide both horizontal and vertical guidance to aircraft. The localizer transmits left and right signals to guide aircraft horizontally along the runway centerline, while the glide path transmits upper and lower signals to guide aircraft vertically along the ideal descent glidepath. Onboard antennas and indicators in the cockpit allow pilots to follow the ILS beams for precise approaches down to decision heights as low as 200 feet during low visibility conditions.
This document discusses aircraft maintenance records and requirements. It emphasizes the importance of accurate documentation and identifies common documentation problems. It outlines requirements for maintenance record content, including descriptions of work performed, completion dates, and signatures. It also discusses issues like poor shift turnovers, non-compliance with airworthiness directives, and the importance of following regulations and procedures for aircraft maintenance.
Dragonair Certificate Program A320 Screening FlightYuuji
This document provides instructions for a flight simulator demonstration of flying an Airbus A320. It begins with an introduction and overview of the simulator activity. It then provides a detailed guide to the Airbus cockpit instrumentation, including explanations of the primary flight display, navigation display, flight management computer, autopilot, and fly-by-wire controls. The document concludes with guidance on performing an ILS approach and landing simulation in the Airbus A320 simulator.
This document provides a description and overview of the autopilot and yaw damper system for a B727-200 aircraft. It describes the major components, including the Sperry SP-50 MB V Automatic Flight Control System, which provides three-axis flight stabilization and automatic approach capability. It details the functions of the yaw, roll, and pitch axes, and describes the components that control and provide inputs to each axis, such as rudder power units, aileron servos, elevator power units, and sensors. The document also notes the locations of components throughout the aircraft.
This document discusses aircraft oil systems. It describes how to check oil levels and temperatures during flight. High or low oil temperatures could indicate issues like blocked lines or improper viscosity. Wet sump systems store oil in a sump integrated into the engine, while dry sump systems store oil externally and use pumps. Pilots should monitor oil pressure and temperature gauges during operation to ensure the system is functioning properly. Proper lubrication and cooling of engine parts is critical.
This document discusses the primary flight controls of aircraft:
1. The elevator controls pitch around the lateral axis using upward and downward deflection. Larger aircraft use hydraulic or electric systems.
2. The rudder controls yaw around the normal axis and is operated by rudder pedals, which also control steering while taxiing. Some aircraft with V-tails use linked ruddervator surfaces.
3. Ailerons control roll around the longitudinal axis and work differentially to bank the aircraft, sometimes assisted by differential rudder inputs to coordinate the turn. Some light aircraft use flaperons.
Airbus a319 a320 a321 aircraft operating manualsn7
This document provides an operations manual for the Airbus A319/320/321 aircraft, summarizing key performance, systems and operational limits. It includes information on weight and balance limits, fuel requirements, avionics and autopilot limits, engine and systems specifications, airspeed limitations for different configurations, and center of gravity envelopes. The manual is intended to provide pilots with essential reference information to safely operate the aircraft.
This document discusses aircraft flight control systems. It describes three main categories of flight controls: primary, secondary, and auxiliary.
Primary flight controls include elevators, ailerons, and the rudder. Elevators control pitch, ailerons control roll, and the rudder controls yaw. Secondary flight controls include trim tabs which help balance aircraft control forces. Auxiliary controls include flaps and other high lift devices which allow aircraft to fly at slower speeds. The document provides details on how each of these various control surfaces and systems function.
Takeoff and Landing | Flight Mechanics | GATE AerospaceAge of Aerospace
This document provides an overview of the topics covered in a presentation on flight mechanics, takeoff, and landing. The core topics include basics of atmosphere, aircraft classification, airplane configuration, flight instruments, aerodynamic forces, and airplane performance including takeoff, landing, climb, descent, stability, and equations of motion. The presentation will focus on takeoff and landing performance, outlining the different segments of ground roll for takeoff and approach/flare/ground roll distances for landing, as well as factors that influence accelerated performance like drag, minimum control speeds, and decision speeds. References for further information are provided.
This chapter provides an overview of aircraft structure and components. It defines key terms like fuselage, wings, empennage, landing gear, and powerplant. It describes basic aerodynamic concepts like thrust, lift, weight, and drag. It explains how control surfaces like ailerons, elevators, and rudders control the aircraft's pitch, roll, and yaw. It briefly discusses different types of aircraft construction materials and methods.
The document provides training material on landing gear for the B727-200 aircraft. It describes the landing gear components and systems, including the main and nose gears, retraction/extension mechanisms, safety sensors, and electrical/electronic modules. It contains detailed sections on the description, operation, and maintenance of the landing gear and related systems. The training material is for student use only and cannot be distributed without permission.
This document defines abbreviations commonly used in airway manuals to provide concise descriptions of aviation terms. It includes over 200 abbreviations ranging from A/A (Air to Air) to Z (Magnetic Course measured from a VOR station). The abbreviations cover a wide variety of aviation topics including navigation aids, airspace designations, airport identifiers, and meteorological terms.
Ground handling services include all the services an aircraft needs while on the ground at an airport. These services include passenger handling at check-in and arrival, ramp services like aircraft and baggage handling, de-icing, and towing, load control and flight operations support before and after flights, cargo and mail warehouse services, security services throughout travel, and various support services required for successful aircraft handling. It is important to hire an experienced ground handling company, such as Transworld Aviation in Zanzibar, to ensure quality airport services.
The Airport Handling Manual 39th Edition includes several key changes and updates:
- Chapters 2 and 6 were significantly revised or sections were removed and consolidated in other manuals.
- Chapters 3, 4, 5, 7, 8, and 9 saw updates to procedures and guidelines around cargo handling, aircraft loading, load planning, aircraft operations, ground handling agreements, and ground support equipment to improve safety, efficiency, and standardization.
- Specific additions included new guidelines for safety performance indicators, occupational health and safety programs, cargo key performance indicators, and the use of pooled ground support equipment.
This document provides guidance on standards and recommended practices for securing civil aviation against unlawful interference. It covers definitions, general principles, organization of national aviation security programs, and components of effective security systems. Key areas discussed include designation of appropriate security authorities, national security legislation and regulations, threat assessment, security training, airport security programs, contingency planning, and international cooperation. The document aims to establish comprehensive security measures to safeguard international air transport.
The document discusses aircraft flight control systems. It describes the primary flight controls which include the elevator, aileron, and rudder control systems. The elevator controls pitch, the ailerons control roll, and the rudder controls yaw. Secondary flight controls include trim tabs that help balance aircraft control forces. Auxiliary controls include flaps, slats, and spoilers which help with lift during takeoff and landing. The document also provides an overview of autopilot systems, how they receive input from sensors and gyros, and how they output movements to flight control surfaces like ailerons and elevators to guide the aircraft without pilot assistance.
The document summarizes the basic control systems of an aircraft, including primary, secondary, and auxiliary flight controls. Primary controls include elevators, ailerons, and rudders which control pitch, roll, and yaw respectively. Secondary controls include trim tabs which help balance aircraft forces. Auxiliary controls include flaps, spoilers, and slats which provide additional lift, especially at lower speeds. The document describes the purpose and function of each control surface.
Alaska Airlines Airbus Study Presentation 2ShawnSmith231
The document provides information about various aircraft systems. It includes 186 slides with details about the Air Data and Inertial Reference System, ADIRS alignment procedures, emergency electrical configurations, oxygen systems, and engine fire detection and extinguishing. Key points covered are the three ADIRUs that supply data to flight instruments, procedures for ADIRS alignment, what is powered during RAT and battery power, and the components involved in detecting and extinguishing an engine fire.
The Instrument Landing System (ILS) uses radio beams to guide aircraft during low visibility approaches and landings. ILS consists of ground-based transmitters that provide both horizontal and vertical guidance to aircraft. The localizer transmits left and right signals to guide aircraft horizontally along the runway centerline, while the glide path transmits upper and lower signals to guide aircraft vertically along the ideal descent glidepath. Onboard antennas and indicators in the cockpit allow pilots to follow the ILS beams for precise approaches down to decision heights as low as 200 feet during low visibility conditions.
This document discusses aircraft maintenance records and requirements. It emphasizes the importance of accurate documentation and identifies common documentation problems. It outlines requirements for maintenance record content, including descriptions of work performed, completion dates, and signatures. It also discusses issues like poor shift turnovers, non-compliance with airworthiness directives, and the importance of following regulations and procedures for aircraft maintenance.
Dragonair Certificate Program A320 Screening FlightYuuji
This document provides instructions for a flight simulator demonstration of flying an Airbus A320. It begins with an introduction and overview of the simulator activity. It then provides a detailed guide to the Airbus cockpit instrumentation, including explanations of the primary flight display, navigation display, flight management computer, autopilot, and fly-by-wire controls. The document concludes with guidance on performing an ILS approach and landing simulation in the Airbus A320 simulator.
This document provides a description and overview of the autopilot and yaw damper system for a B727-200 aircraft. It describes the major components, including the Sperry SP-50 MB V Automatic Flight Control System, which provides three-axis flight stabilization and automatic approach capability. It details the functions of the yaw, roll, and pitch axes, and describes the components that control and provide inputs to each axis, such as rudder power units, aileron servos, elevator power units, and sensors. The document also notes the locations of components throughout the aircraft.
This document discusses aircraft oil systems. It describes how to check oil levels and temperatures during flight. High or low oil temperatures could indicate issues like blocked lines or improper viscosity. Wet sump systems store oil in a sump integrated into the engine, while dry sump systems store oil externally and use pumps. Pilots should monitor oil pressure and temperature gauges during operation to ensure the system is functioning properly. Proper lubrication and cooling of engine parts is critical.
This document discusses the primary flight controls of aircraft:
1. The elevator controls pitch around the lateral axis using upward and downward deflection. Larger aircraft use hydraulic or electric systems.
2. The rudder controls yaw around the normal axis and is operated by rudder pedals, which also control steering while taxiing. Some aircraft with V-tails use linked ruddervator surfaces.
3. Ailerons control roll around the longitudinal axis and work differentially to bank the aircraft, sometimes assisted by differential rudder inputs to coordinate the turn. Some light aircraft use flaperons.
Airbus a319 a320 a321 aircraft operating manualsn7
This document provides an operations manual for the Airbus A319/320/321 aircraft, summarizing key performance, systems and operational limits. It includes information on weight and balance limits, fuel requirements, avionics and autopilot limits, engine and systems specifications, airspeed limitations for different configurations, and center of gravity envelopes. The manual is intended to provide pilots with essential reference information to safely operate the aircraft.
2. Spesifikasi pesawat
Pesawat XXX memiliki spesifikasi sebagai berikut :
Wing span = 42.5 ft
Wing Area = 182 ft2
Gross weight = 3150 lb
Normal capacity = 75 gallon of gasoline
Power plan of two piston engine of 150 hp
(each engine) at sea level.
Fuel Consumption = 0.48 lb/(hp)(h)
Parasite drag Coefficient, 𝐶𝑑. 0 = 0.031
Oswald efficiency factor, ℯ =0.9
Propeller efficiency = 0.85
μ = 0.025 dan ρ = 1.225
The wing are 7 ft above the ground
3. Rate of Climb
Rate of climb (R/C) merupakan kecepatan vertical yang dibentuk oleh sebuah
pesawat. R/C dipengaruhi oleh nilai kecepatan pesawat itu sendri.
5. Rate of Climb
Rate of Climb =
𝑝𝑜𝑤𝑒𝑟 𝑎𝑣𝑎𝑖𝑙𝑎𝑏𝑙𝑒 −𝑝𝑜𝑤𝑒𝑟 𝑟𝑒𝑞𝑢𝑖𝑟𝑒𝑑
𝑊
Power available = (efisiensi propeller) x (power) = 0.85x(2x150) = 255hp
6. Gliding
Gliding merupakan suatu kondisi pesawat terbang meluncur dengan sudut
tertentu dan tidak memiliki gaya dorongan (poweroff).
7. Gliding
R merupakan jarak yang diperlukan sebuah pesawat
sejak power off sampai ground.
Dimana h merupakan ketinggian pesawat ketika poweroff atau
thrust = 0
8. Rate of Climb
Formula untuk mencari nilai rate of climb adalah
𝑃𝑜𝑤𝑒𝑟 𝑎𝑣𝑎𝑖𝑙𝑎𝑏𝑙𝑒 −𝑃𝑜𝑤𝑒𝑟 𝑟𝑒𝑞𝑢𝑖𝑟𝑒𝑑
𝑊𝑒𝑖𝑔ℎ𝑡
Power available pada pesawat XXX ini sebesar, Pa = ŋ.P.
maka Pa = (0.85).(2x150 hp) = 255 horsepower.
Power required, Pr = 𝑞. 𝑆.
𝑊𝑒𝑖𝑔ℎ𝑡
(
𝐶𝑙
𝐶𝑑
)
. 𝑉∞
Nilai 𝐶𝑙 didapatkan dari rumus 𝐶𝑙 =
𝑊𝑒𝑖𝑔ℎ𝑡
1
2
ρ𝑉²
Kemudain nilai 𝐶𝑑 = 𝐶𝑑. 0 +
𝐶𝑙²
πℯ𝐴𝑅
dimana nilai 𝐶𝑑. 0 adalah 0.0031.
Maka Pr = 𝑞. 𝑆.
𝑊
𝑊𝑒𝑖𝑔ℎ𝑡
𝑞
𝐶𝑑.0+
𝐶𝑙2
πℯ𝐴𝑅
. 𝑉∞
𝑞 𝑑𝑦𝑛𝑎𝑚𝑖𝑐 𝑝𝑟𝑒𝑠𝑠𝑢𝑟𝑒 =
1
2
𝜌𝑉2
𝐴𝑅 𝐴𝑠𝑝𝑒𝑐𝑡 𝑅𝑎𝑡𝑖𝑜 =
𝑏2
𝑠
12. Kesimpulan
Pada pesawat XXX ini jika nilai Pr=Pa, maka kecepatan maksimum pesawat
sekitar 555ft/s. Dan Mach number pesawat adalah Vmax/a = 555/1117 =
0.51M
Rate of Climb Max = 40.22454514ft/s = 2413.473 ft/min Pada kecepatan
200ft/s
Gliding angle 1/(L/D)max = tanθ 0.021496322 = 1.23°
Maka jarak pesawat menuju ground dengan asumsi poweroff (thrust = 0) pada
ketinggian 10000ft adalah Rmax = h.(L/D)max = 10000.(46.666667) =
466666.67 ft.
Editor's Notes
Perkenalan diri, mata kuliah yang dimaksud, bapak dadi selaku dosen perkuliahan kendali terbang, ucapan terima kasih atas kesempatan memberikan presentasi kali ini, jelaskan mengenai kondisi pesawat ketika terbang dan sedikit performance pesawat. kasus ini yaitu rate of climb dan gliding.
Penjelasan rate of climb. Komponen apa saja yang dierlukan ketika rate of climb yaitu kecepatan dan sin θ (sindemi) karena kita telah mebgetahui kecepatan pesawat, maka kita bias menghitung berapa kah kecepatan vertical pesawat dengan v.sinθ.
Selanjutnya kita akan membahas mengenai korelasi antara kecepatan pesawat dengan power dari engine pesawat. Rate of climb adalah excess power dibagi dengan weight (berat pesawat). Dimana pengertian Excess power adalah jumlah power yang lebih atau sisa power yang tersedia dari power yang diperlukan oleh pesawat.
Dengan kata lain, excess power merupakan power available atau power yang tersedia dikurangi dengan power required. Power available setiap engine pada pesawat xxx ini sebesar 150hp, pesawat xxx ini memiliki 2 buah engine dengan tambahan sebuah propeller. Maka power available pesawat ini adalah 300hp dikalikan dengan efisiensi propeller yaitu sebesar 0.85 dan power available total sebesar 255hp..
Kondisi selanjutnya adalah kondisi gliding. Kondisi gliding merupakan kondisi dimana pesawat terbang meluncur dengan gaya dorong 0 dan membentuk sudut dengan besaran tertentu. Komponen yang terdapat ketika kondisi gliding hanya drag dan lift. Drag akan mebentuk sudut sebesar sinθ dan lift sebesar cosθ. Maka ketika gliding, suddut minimum pesawat sebesar tanθ = 1/(L/D)max. *tan θ berasal dari flight path dan horizontal.
Ketika gliding, pesawat didesign sedemikian rupa agar mendapatkan prestasi terbang gliding yang bagus dengan memiliki nilai sudut tanθ minimum. Jarak kemampuan gliding sebuah pesawat terbang atau R dapat dihitung dengan ketinggian pesawat ketika poweroff dikalikan dengan ratio L/D maksimum.
Berikut ini merupakan kesimpulan formula kita gunakan untuk menghitung rate of climb pesawat XXX.
Tabel diatas merupakan hasil perhitungan yang saya hitung menggunakan Ms.Excell. Perhitungan ini sebenarnya di mulai dari kecepatan 0 – 1000ft/s. bias kita lihat bahwa nilai ratio cl/cd max sebesar 46.66 dicapai pada kecepatan 200ft/s. kemudian untuk sudut gliding yang diperoleh sebesar 1.23° dengan kemampuan gliding sejauh 466.666.67 ft.
Disini kita lihat gambaran berupa grafik power dan Rate of Climb pesawat XXX. Kita lihat perpotongan antara power available dan power required terjadi pada kecepatan kurang dari 600ft/s. perpotongan tersebut mengindikasikan keccepatan maksimum yang mampu ditempuh pesawat XXX ini. Selanjutnya pada grafik rate of climb, kita memiliki nilai rate of climb maksimum sebesar 2413.5 ft/min pada kecepatan sekitar 200 ft/s.