Mc Donnell Douglas F-4E Blk.41 Phantom II (J79-GE-17)
|
|
|
- Annabel Pope
- 6 years ago
- Views:
Transcription
1 A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r PERFORMANCE ANALYSIS Mc Donnell Douglas F-4E Blk.41 Phantom II (J79-GE-17) CAUTION STATEMENT : This document is to be use only for simulation. Do not try to apply the procedures and or advices contained in it if you have the opportunity to fly this plane in real life. By the way, if you had (or still have) flew this aircraft, your comments, criticism and more are welcome LICENSE : This document has been created by J.M. LANGERON / TOPOLO, ( all the values used to model the aircraft behavior have been computed by him, like all performance charts presented here. If you want to use these data, or part of it, please contact the author by personal message to TOPOLO on check-six forum: ( I 1-1
2 A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Level Flight Envelope I 1-2
3 Alt (ft) Alt (ft) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Level Flight Envelope 65, 6, 55, 5, Level Flight Enveloppe Full AB Clean GW = 38,517 lbs 45, 4, 35, 3, 4xAIM-7E + 2xAIM-9D + ALQ-71 GW = 41,558 lbs 25, 2, 15, 1, 5, 75 Kts (IAS) from SL to 3,ft 7Kts over , MILL Power Mach Level Flight Enveloppe MIL Power 6, 55, Clean GW = 38,517 lbs 5, 45, 4, 35, 3, 25, 2, 15, 1, 5, 4xAIM-7E + 2xAIM-9D + ALQ-71 GW = 41,558 lbs 75 Kts (IAS) from SL to 3,ft 7Kts over Mach I 1-3
4 A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance Engine : J79-GE-17 4xAIM-7E + 2xAIM-9D + ALQ-71 5% internal fuel GW= 41,558 lbs Load Factor limited to 5.58G (AIM-9 under LAU-7A/A on station 2) IAS limited to 75Kts under 25,ft, 65Kts over 4,ft (ALQ-71/QRC-16-1 on station 9) I 1-4
5 Sustained Turn rate (deg/s) Maximum instantaneous turn rate (deg/s) Turn Rate Summary A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r 4xAIM-7E + 2xAIM-9D + ALQ-71 GW=41,558 lbs Maximum Available Turn Rate , 2, 3, 4, Mach number Maximum Sustained Turn rate (deg/s) 1, 2, 3, 4, Mach number I - 1-5
6 Sustained Load Factor (Ng) Maximum Available Load Factor (Ng) Load Factor Summary A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r 4xAIM-7E + 2xAIM-9D + ALQ-71 GW=41,558 lbs Maximum Available Load Factor 1, 2, 3, 4, Mach number Maximum Sustained Load Factor (Ng) 1, 2, 3, 4, Mach number I - 1-6
7 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance Sea Level 4xAIM-7E + 2xAIM-9D + ALQ-71 GW=41,558 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 17.4 deg/s Max. Sustained Turn Rate = 13.2 deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-7
8 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance 5, ft 4xAIM-7E + 2xAIM-9D + ALQ-71 GW=41,558 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 16.2 deg/s Max. Sustained Turn Rate = 12. deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-8
9 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance 1, ft 4xAIM-7E + 2xAIM-9D + ALQ-71 GW=41,558 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 14.9 deg/s Max. Sustained Turn Rate = 1.8 deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-9
10 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance 15, ft 4xAIM-7E + 2xAIM-9D + ALQ-71 GW=41,558 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 13.7deg/s Max. Sustained Turn Rate = 9.1 deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-1
11 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance 2, ft 4xAIM-7E + 2xAIM-9D + ALQ-71 GW=41,558 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 12.6deg/s Max. Sustained Turn Rate = 7.6 deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-11
12 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance 25, ft 4xAIM-7E + 2xAIM-9D + ALQ-71 GW=41,558 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 11.3 deg/s Max. Sustained Turn Rate = 6.5 deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-12
13 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance 3, ft 4xAIM-7E + 2xAIM-9D + ALQ-71 GW=41,558 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 1.2 deg/s Max. Sustained Turn Rate = 5.4 deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-13
14 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance 35, ft 4xAIM-7E + 2xAIM-9D + ALQ-71 GW=41,558 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 9.5 deg/s Max. Sustained Turn Rate = 4. deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-14
15 A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Climb Performance 4xAIM-7E + 2xAIM-9D + ALQ-71 5% internal fuel GW= 41,558 lbs I 1-15
16 Climb Angle (deg) Excess Specific Power (ft/s) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r 4xAIM-7E + 2xAIM-9D + ALQ-71 GW=41,558 lbs Instantaneous Constant Speed Climb Rate , 1, 15, 2, 25, 3, 35, 4, 45, Mach 9. Constant Speed Climb Angle , 1, 15, 2, 25, 3, 35, 4, Mach I
17 Climb Angle (deg) Excess Specific Power (ft/s) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r MIL Power Instantaneous Constant Speed Climb Rate 4xAIM-7E + 2xAIM-9D + ALQ-71 GW=41,558 lbs , 1, 15, 2, 25, 3, 35, 4, 45, Mach Constant Speed Climb Angle , 1, 15, 2, 25, 3, 35, 4, Mach I
18 A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Acceleration Performances 4xAIM-7E + 2xAIM-9D + ALQ-71 5% internal fuel GW= 41,558 lbs I 1-18
19 Time (s) Time (s) Acceleration Diagram A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r 1, 2, 4xAIM-7E + 2xAIM-9D + ALQ-71 GW=41,558 lbs 18 Acceleration (Max Thrust AB) , ft , ft 45 3 Sea Level , 3, 36, Mach 18 Acceleration (Max Thrust AB) , ft , ft 36, ft Mach I 1-19
20 A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance Engine : J79-GE-17 4xAIM-7E 5% internal fuel GW= 4,337lbs I 1-2
21 Sustained Turn rate (deg/s) Maximum instantaneous turn rate (deg/s) Turn Rate Summary A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r 4xAIM-7E GW=4,337 lbs Maximum Available Turn Rate , 2, 3, 4, 15. Maximum reached without AoA limit (Stall speed) Ng < 8.8 for mach number <.72 Ng < 6.18 for mach number > Mach number Maximum Sustained Turn rate (deg/s) 1, 2, 3, 4, Mach number I
22 Sustained Load Factor (Ng) Maximum Available Load Factor (Ng) Load Factor Summary A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r 4xAIM-7E GW=4,337 lbs Maximum Available Load Factor 1, 2, 3, 4, Maximum reached without AoA limit (Stall speed) Ng < 8.8 for mach number <.72 Ng < 6.18 for mach number > Mach number Maximum Sustained Load Factor (Ng) 1, 2, 3, 4, Mach number I
23 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance Sea Level 4xAIM-7E GW=4,337 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G 22. Max. Instantaneous Turn Rate = 21.4 deg/s Max. Sustained Turn Rate = 14.4 deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-23
24 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance 5, ft 4xAIM-7E GW=4,337 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 19.8 deg/s Max. Sustained Turn Rate = 13.deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-24
25 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance 1, ft 4xAIM-7E GW=4,337 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 18.1 deg/s Max. Sustained Turn Rate = 11.2 deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-25
26 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance 15, ft 4xAIM-7E GW=4,337 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 16.3 deg/s Max. Sustained Turn Rate = 9.5 deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-26
27 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance 2, ft 4xAIM-7E GW=4,337 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 14.2 deg/s Max. Sustained Turn Rate = 7.9 deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-27
28 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance 25, ft 4xAIM-7E GW=4,337 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 12.5 deg/s Max. Sustained Turn Rate = 6.8 deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-28
29 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance 3, ft 4xAIM-7E GW=4,337 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 11.2 deg/s Max. Sustained Turn Rate = 5.7 deg/s MAXIMUM AIR SPEED CAS (Kts) I 1-29
30 Turn Rate (degree per second) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Turn Performance 35, ft 4xAIM-7E GW=4,337 lbs 24. 2G 3G 4G 5G 6G 7G 8G 9G Max. Instantaneous Turn Rate = 1.2 deg/s Max. Sustained Turn Rate = 4.2 deg/s +2 MAXIMUM AIR SPEED CAS (Kts) I 1-3
31 A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Climb Performance Engine : J79-GE-17 4xAIM-7E 5% internal fuel GW= 4,337 lbs I 1-31
32 Excess Specific Power (ft/s) Climb Angle (deg) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r 4xAIM-7E GW=4,337 lbs Instantaneous Constant Speed Climb Rate , 1, 15, 2, 25, 3, 35, 4, 45, Mach Constant Speed Climb Angle , 1, 15, 2, 25, 3, 35, 4, Mach I
33 Excess Specific Power (ft/s) Climb Angle (deg) A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r MIL Power 4xAIM-7E GW=4,337 lbs Instantaneous Constant Speed Climb Rate , 1, 15, 2, 25, 3, 35, 4, 45, Mach Constant Speed Climb Angle , 1, 15, 2, 25, 3, 35, 4, Mach I
34 A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r Acceleration Performances Engine : J79-GE-17 4xAIM-7E 5% internal fuel GW= 4,337 lbs I 1-34
35 Time (s) Time (s) Acceleration Diagram A1-Mc Donnell Douglas F-4E Blk.41 -NFM--r 1, 2, 4xAIM-7E GW=4,337 lbs 18 Acceleration (Max Thrust AB) , ft Sea Level 2, ft , 3, 36, Mach 18 Acceleration (Max Thrust AB) , ft , ft 36, ft Mach I 1-35
Mc Donnell Douglas F-4D Blk.37 Phantom II (J79-GE-15)
A1-Mc Donnell Douglas F-4D Blk.37-NFM--r1 PERFORMANCE ANALYSIS Mc Donnell Douglas F-4D Blk.37 Phantom II (J79-GE-15) CAUTION STATEMENT : This document is to be use only for simulation. Do not try to apply
Basic hypothesis. Subjective position may give less Drag at high Mach number to the Typhoon and better Lift at high AoA (>20) for the Rafale.
vs Rafale Basic hypothesis Rafale C and share the same aerodynamic configuration, means same CL (lift) and CD (drag) coefficients law [Cx(Mach, AoA)]. This is known as not realistic, but I do not have
Compared Air Combat Performances analysis Mig-21 versus F-4 Phantom II Part 1
Compared Air Combat Performances analysis Mig-21 versus F-4 Phantom II Part 1 LICENSE: This document has been created by J.M. LANGERON / TOPOLO, (http://topolo.free.fr/). All the values used to model the
Compared Air Combat Performances analysis Mig-21 versus F-5E
Compared Air Combat Performances analysis Mig-21 versus F-5E LICENSE: This document has been created by J.M. LANGERON / TOPOLO, (http://topolo.free.fr/). All the values used to model the aircraft behavior
AIR TRACTOR, INC. OLNEY, TEXAS
TABLE OF CONTENTS LOG OF REVISIONS... 2 DESCRIPTION... 4 SECTION 1 LIMITATIONS... 5 SECTION 2 NORMAL PROCEDURES... 8 SECTION 3 EMERGENCY PROCEDURES... 8 SECTION 4 MANUFACTURER'S SECTION - PERFORMANCE...
Welcome to the Airbus A380 Basic Manual for Virtual Air Cadet Airlines.
Welcome to the Airbus A380 Basic Manual for Virtual Air Cadet Airlines. Performance figures: Max operating speed: 340kts / M0.89 Max gear speed: 250kts / M0.55 Max flap speeds: Code: Select all Flaps Speed
Fuel Saving by Gradual Climb Procedure. Ryota Mori (Electronic Navigation Research Institute)
Fuel Saving by Gradual Climb Procedure Ryota Mori (Electronic Navigation Research Institute) 1 Single Flight Optimal Trajectory Optimal climb CAS: 320 kt TOC (Top of climb) Fuel optimal altitude increases
USAF Strike Fighters. An analysis of range, stamina, turning, and acceleration
USAF Strike Fighters An analysis of range, stamina, turning, and acceleration The Contenders There are currently slated to be three USAF strike aircraft in the 2020 timeframe F-15E Strike Eagle One of
European Aviation Safety Agency
R-TCDS.A.014 Page 1/10 European Aviation Safety Agency EASA RESTRICTED TYPE-CERTIFICATE DATA SHEET EASA.A.014 AIRBUS A300-600ST Manufacturer: AIRBUS 1 Rond-point Maurice Bellonte 31707 BLAGNAC FRANCE For
LATERAL WEIGHT ASYMMETRY LIMITS. Catapult takeoff
LATERAL WEIGHT ASYMMETRY LIMITS Field takeoff Catapult takeoff Weight board 36,000 lbs Weight board 37,000 lbs Inflight conditions 22,000 ft-lbs 6,000 ft-lbs 22,000 ft-lbs 26,000 ft-lbs Asymmetric jettison/normal
AE 451 Aeronautical Engineering Design Final Examination. Instructor: Prof. Dr. Serkan ÖZGEN Date:
Instructor: Prof. Dr. Serkan ÖZGEN Date: 11.01.2012 1. a) (8 pts) In what aspects an instantaneous turn performance is different from sustained turn? b) (8 pts) A low wing loading will always increase
SECTION 17 AIRCRAFT PROCEDURES
SECTION 17 AIRCRAFT 1 of 15 PILOT MEMO STANDARD CONFIGURATIONS Configuration CLEAN AIRCRAFT STANDARD AIR TO AIR Detailed Payload Full internal fuel; guns, brake chute and countermeasures (no extra Eclair
General Dynamics F-16 Fighting Falcon
General Dynamics F-16 Fighting Falcon http://www.globalsecurity.org/military/systems/aircraft/images/f-16c-19990601-f-0073c-007.jpg Adam Entsminger David Gallagher Will Graf AOE 4124 4/21/04 1 Outline
XIV.C. Flight Principles Engine Inoperative
XIV.C. Flight Principles Engine Inoperative References: FAA-H-8083-3; POH/AFM Objectives The student should develop knowledge of the elements related to single engine operation. Key Elements Elements Schedule
Engine Performance Analysis
Engine Performance Analysis Introduction The basics of engine performance analysis The parameters and tools used in engine performance analysis Introduction Parametric cycle analysis: Independently selected
PRODUCT CODE Av3 FLIGHT PLANNING EXAM 2 WORKING. by Rob Avery
FP exam 2 working. PRODUCT CODE Av3 FLIGHT PLANNING EXAM 2 WORKING by Rob Avery INTELLECTUAL PROPERTY OF ROB AVERY PLEASE SHOW PROFESSIONALISM BY NOT MAKING ILLEGAL COPIES. Flight Planning Practice exam
USAF Strike Fighters. An analysis of range, stamina, turning, and acceleration By Spurts
USAF Strike Fighters An analysis of range, stamina, turning, and acceleration By Spurts The Contenders There are currently slated to be three USAF strike aircraft in the 2020 timeframe F-15E Strike Eagle
FSFlyingSchool2010 Cessna 172 Detail Pack
FSFlyingSchool2010 Cessna 172 Detail Pack Manual Web: www.fsflyingschool.com Support: [www.fsflyingschool.com/forum] Forum: [www.fsflyingschool.com/forum] Sales: [sales@fsflyingschool.com] Published: June
FLIGHT PLANNING EXAM 4 WORKING
Copyright Avfacts 1999. Page 1. FLIGHT PLANNING EXAM 4 WORKING Q 1. This is a STEP CLIMB question. Refer to B727 manual 3 engine Altitude Capability section on page 2-14. ISA Step 1. Find maximum arrival
by Greg Whiley Aussie Star Flight Simulation
Flying the BAe 146 200/300 Version 2 by Greg Whiley Aussie Star Flight Simulation INTENTIALLY LEFT BLANK Greg Whiley Aussie Star Flight Simulation 2 Version Date Revision Version 1.0 25 June 2014 Original
INCORPORA:1EO. PO Box Shannon Lane Priest River, FAA APPROVED
INCORPORA:1EO FAA APPROVED Document A-1 0023.., Page 1 of. 9 Rev, (see rev. page) SUPPLEMENTAL AIRPLANE FLIGHT MANUAL FOR CESSNA 180J & 180K SERIES FLOATPLANES Modified with Kenmore Air Harbor STC # SA649NW
ADTS550F. Your touch, our technology. GE Measurement & Control. (ADTS552F, ADTS553F, ADTS554F) Wireless ADTS500 Series Easy-to-Use Pitot Static Tester
GE Measurement & Control ADTS550F (ADTS552F, ADTS553F, ADTS554F) Wireless ADTS500 Series Easy-to-Use Pitot Static Tester Features ADTS Touch hand terminal with WiFi and Bluetooth wireless technology (backup
LOW BOOM FLIGHT DEMONSTRATOR (LBFD)
Concept Development of the Quiet Supersonic Technology Aircraft LOW BOOM FLIGHT DEMONSTRATOR (LBFD) Peter Iosifidis Program Manager Overview Background Why Now for a Quiet Supersonic Technology X-plane?
Weight Effects Part 1
Weight Effects Part 1 David F. Rogers Copyright c 1997-1999 David F. Rogers. All rights reserved. Most of us normally operate our aircraft at less than gross weight, yet weight significantly affects the
Classical Aircraft Sizing II
Classical Aircraft Sizing II W. H. Mason Advanced Concepts from NASA TM-1998-207644 slide 1 11/18/08 Previously (Sizing I) Mission definition Basic Sizing to Estimate TOGW Examples Now: More Details and
Problem Statement. After losing hydraulic systems when engine #1 detached during takeoff.
Problem Statement Report umber RCA-28-07-17-114 RCA Owner Chris Eckert Report Date 7/28/2017 RCA Facilitator Brian Hughes Focal Point: Crashed - 273 Fatalities When Start Date: 5/25/1979 End Date: 5/25/1979
Lateral Directional Flight Considerations
Lateral Directional Flight Considerations This section discusses the lateral-directional control requirements for various flight conditions including cross-wind landings, asymmetric thrust, turning flight,
Van s Aircraft RV-7A. Pilot s Operating Handbook N585RV
Van s Aircraft RV-7A Pilot s Operating Handbook N585RV PERFORMANCE SPECIFICATIONS SPAN:..25 0 LENGTH...20 4 HEIGHT:.. 7 10 SPEED: Maximum at Sea Level...180 knots Cruise, 75% Power at 8,000 Ft...170 knots
RFC Dallas, Inc. AIRCRAFT QUESTIONNAIRE (9/25/2016) "A Safe Pilot Knows His Equipment"
RFC Dallas, Inc. AIRCRAFT QUESTIONNAIRE (9/25/2016) "A Safe Pilot Knows His Equipment" NAME: Date: Aircraft: Cessna 182Q Registration Number: N631S Serial Number: The purpose of this questionnaire is to
ELECTRIC POWER TRAINS THE KEY ENABLER FOR CONTRA ROTATING PROPELLERS IN GENERAL AVIATION (& VICE VERSA)
ELECTRIC POWER TRAINS THE KEY ENABLER FOR CONTRA ROTATING PROPELLERS IN GENERAL AVIATION (& VICE VERSA) ATI D3 EVENT 8 TH MAY 2018 THE EMERGENCE OF ELECTRIFICATION IN AEROSPACE NICK SILLS, CONTRA ELECTRIC
AN ADVANCED COUNTER-ROTATING DISK WING AIRCRAFT CONCEPT Program Update. Presented to NIAC By Carl Grant November 9th, 1999
AN ADVANCED COUNTER-ROTATING DISK WING AIRCRAFT CONCEPT Program Update Presented to NIAC By Carl Grant November 9th, 1999 DIVERSITECH, INC. Phone: (513) 772-4447 Fax: (513) 772-4476 email: carl.grant@diversitechinc.com
System Normal Secondary Direct. All 3 PFC work in parallel. available. Pitch Normal Secondary Direct. Pitch maneuver command.
Flight s System Normal Secondary Direct Primary Flight Computers (PFC) Three Primary Flight Computers use control wheel and pedal inputs from the pilot to electronically the primary flight control surfaces
1. Ship Name. 5. Type 6. Size Class/ Description. Damage Points. Surface Speed. Submerged Speed. Embarked Aircraft
Ship Reference Sheet 3. Configuration Date Function 4. Class V 1. Ship 5. Type 6. Size Class Description age Point Effects Percent age % 25% 5% 75% 9% 1% Submerged Speed 7. Crew 8. Signature 2. Armor Class
j2 Universal Tool Kit Software in a Performance Prediction Role
j2 Universal Tool Kit Software in a Performance Prediction Role The j2 Universal Tool-Kit Performance Plug-in Derives Even More Value From The Leading Aircraft Design, Analysis and Aircraft Modelling Software
A310 MEMORY ITEMS Last Updated: 20th th October 2011
A310 MEMORY ITEMS Last Updated: 20th th October 2011 1. Emergency Descent: Crew Oxygen Mask ON Crew Communication (Headsets) Establish Turn Initiate Descent Initiate o It is recommended to descend with
ATPL Workbook. ATPL Advanced Aerodynamics, Performance and Systems Knowledge (Aeroplane)
ATPL Workbook Subjects: ATPL Advanced Aerodynamics, Performance and Systems Knowledge (Aeroplane) This version of the workbook is for training purposes. An examination version will be provided at the examination
Blended Winglets on an E-Racer Canard Aircraft
Blended Winglets on an E-Racer Canard Aircraft Performance Increase? Marc J. Zeitlin / Jack Morrison July 26 th, 2007 2:30 PM 3:45 PM Forum Tent 06 Sporty s Pavilion July 19, 2007 Canard Forum Slide Show
AIRLINE TRANSPORT PILOTS LICENSE ( FLIGHT PERFORMANCE AND PLANNING)
032 01 00 00 PERFORMANCE OF SINGLE-ENGINE AEROPLANES NOT CERTIFIELD UNDER JAR/FAR 25 (LIGHT AEROPLANES) PERFORMANCE CLASS B 032 01 01 00 Definitions of terms and speeds used Define the following terms
BAYLOR UNIVERSITY DEPARTMENT OF ENGINEERING. EGR 4347 Analysis and Design of Propulsion Systems Fall 2002 ASSIGNMENT GUIDELINES
BAYLOR UNIVERSITY DEPARTMENT OF ENGINEERING EGR 4347 Analysis and Design of Propulsion Systems Fall 2002 Design Project I Dr Van Treuren 100 points ASSIGNMENT GUIDELINES For this assignment, you may work
FLIGHT CONTROLS SYSTEM
FLIGHT CONTROLS SYSTEM DESCRIPTION Primary flight control of the aircraft is provided by aileron, elevator and rudder control surfaces. The elevator and rudder control surfaces are mechanically operated.
Part 1 Aerodynamic Theory COPYRIGHTED MATERIAL
Part 1 Aerodynamic Theory COPYRIGHTED MATERIAL 5 6 1 Preliminaries Before studying the chapters dealing with the aerodynamics of each phase of flight, it is essential to understand various definitions
Test Flying should only be performed by a pilot who is licensed, rated and experienced on the aircraft type.
Test Flying Procedure: Test Flying should only be performed by a pilot who is licensed, rated and experienced on the aircraft type. In particular, the test pilot should have recently demonstrated an ability
KING AIR MODEL C90/C90A
PILOT S OPERATING HANDBOOK and FAA-Approved Airplane Flight Manual Supplement for the KING AIR MODEL C90/C90A Equipped with Raisbeck Engineering: - STC SA3593NM - STC SA4010NM - STC SA3593NM Increased
David s Flight Simulator Operations Manual
DPW Solutions David s Flight Simulator Operations Manual Draft 0.2 David Woolterton Update 10/5/2016 Table of Contents Pre-Start Checklist... 2 Startup Checklist... 3 Before Taxi Checklist... 3 Taxi Checklist...
North American F-86F Sabre USER MANUAL. Virtavia F-86F Sabre DTG Steam Edition Manual Version 1
North American F-86F Sabre USER MANUAL 0 Introduction The F-86 Sabre was a natural replacement for the F-80 Shooting Star. First introduced in 1949 for the United States Air Force, the F-86 featured excellent
Boeing /-200/-200A Limitations
Boeing 727-100/-200/-200A Limitations The information provided in this document is to be used during simulated flight only and is not intended to be used in real life. Attention VA's - you may post this
Boeing B-47 Stratojet USER MANUAL. Virtavia B-47E Stratojet DTG Steam Edition Manual Version 2
Boeing B-47 Stratojet USER MANUAL 0 Introduction The Boeing B-47 was the first swept-wing multi-engine bomber in service with the USAF. It was truly a quantum leap in aviation history, and is the forerunner
Effect of ZFW / ZFWCG on Aircraft Operations
Operational Liaison Meeting Fly-By-Wire Aircraft 2004 Effect of / on Aircraft Operations Customer Services Contents Single-Aisle (SA) FM Architecture FAC Computation If Incorrect entered on the If Incorrect
Welcome to Aerospace Engineering
Welcome to Aerospace Engineering DESIGN-CENTERED INTRODUCTION TO AEROSPACE ENGINEERING Notes 5 Topics 1. Course Organization 2. Today's Dreams in Various Speed Ranges 3. Designing a Flight Vehicle: Route
P/N 135A FAA Approved: 5/14/2007 Section 9 Initial Release Page 1 of 10
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR MT PROPELLER INSTALLATION Serial No: Registration No: When the MT Propeller is installed on the Liberty Aerospace XL2, this supplement is applicable and
CIRRUS AIRPLANE MAINTENANCE MANUAL
CENTRAL WARNING SYSTEMS 1. GENERAL This section describes the Central Warning Systems which consists of a Crew Alerting System (CAS) and related sensors and switches. A. Crew Alerting System Aircraft annunciations
Flight Test Evaluation of C-130H Aircraft Performance with NP2000 Propellers
Flight Test Evaluation of C-130H Aircraft Performance with NP2000 Propellers Lance Bays Lockheed Martin - C-130 Flight Sciences Telephone: (770) 494-8341 E-Mail: lance.bays@lmco.com Introduction Flight
TECNAM P2004 BRAVO N128LS
TECNAM P2004 BRAVO N128LS GENERAL INFORMATION NORMAL PROCEDURES TIME SENSITIVE EMERGENCY TECNAM P2004 BRAVO CHECKLIST [FLIGHT PLAN DESIGNATION IS BRAV ] EMERGENCY CONTACT The following are First Landings'
AIRCRAFT FAMILIARIZATION. Some questions may not apply to the aircraft you are flying.
541-895-5935 Name Date AIRCRAFT FAMILIARIZATION Note: If this information is not provided in the aircraft s flight manual give it your best guess. Some questions may not apply to the aircraft you are flying.
Classical Aircraft Sizing I
Classical Aircraft Sizing I W. H. Mason from Sandusky, Northrop slide 1 Which is 1 st? You need to have a concept in mind to start The concept will be reflected in the sizing by the choice of a few key
Singapore Airlines Flight 368 Engine Fire. Ng Junsheng Head (Technical)/Senior Air Safety Investigation Transport Safety Investigation Bureau
Singapore Airlines Flight 368 Engine Fire Ng Junsheng Head (Technical)/Senior Air Safety Investigation Transport Safety Investigation Bureau 3 rd Annual Singapore Aviation Safety Seminar 29 March 2017
TECNAM P92 EAGLET N615TA TECNAM P92 EAGLET CHECKLIST [FLIGHT PLAN DESIGNATION IS ECHO ]
![TECNAM P92 EAGLET N615TA TECNAM P92 EAGLET CHECKLIST [FLIGHT PLAN DESIGNATION IS ECHO ]](/thumbs/86/93080937.jpg "TECNAM P92 EAGLET N615TA TECNAM P92 EAGLET CHECKLIST [FLIGHT PLAN DESIGNATION IS ECHO ]")
TECNAM P92 EAGLET CHECKLIST [FLIGHT PLAN DESIGNATION IS ECHO ] EMERGENCY CONTACT The following are First Landings' emergency contact telephone numbers. We ask that you call the numbers in the order listed.
AIRCRAFT INSPECTION REPORT. For CESSNA 172 RG
OSU, MAE 4223 Class Report 4 May 2001 AIRCRAFT INSPECTION REPORT For CESSNA 172 RG i This report documents the results of simulated FAA airworthiness flight testing conducted in accordance with Note and
A-6E Intruder USER MANUAL. Virtavia A-6E Intruder DTG Steam Edition Manual Version 2.0
A-6E Intruder USER MANUAL 0 Introduction The Grumman A-6 was the US Navy's premier precision strike aircraft for over 30 years. First introduced in 1963, the A-6 saw extensive service in Vietnam and continued
The Fokker S-14 Mach-trainer for FS9,FSX and Prepar3D
The Fokker S-14 Mach-trainer for FS9,FSX and Prepar3D Fokker S-14 at Twente airforce base History The Fokker S-14 Mach-trainer was the first purpose designed and built side by side jet trainer. First flight
Mike Gibbons Paul Summers John Murnane
Outpacing threats in a 2030+ A2/AD environment affordably! RROI 13-01092 - BDS Mike Gibbons Paul Summers John Murnane August 27, 2013 Capability Continuum Evolution of the Super Hornet Mission Systems
CHAPTER 17 LIMITATIONS TABLE OF CONTENTS
CHAPTER 17 LIMITATIONS TABLE OF CONTENTS INTRODUCTION... 5 GENERAL... 5 Flight Crew... 6 Configuration... 6 Optional Equipment... 6 Doors Opened / Removed... 6 Passenger Seats... 6 Cargo... 7 Weight and
Central Warning Systems
CIRRUS AIRPLANE MAINTENANCE MANUAL Central Warning Systems CHAPTER 31-50: CENTRAL WARNING SYSTEMS GENERAL 31-50: CENTRAL WARNING SYSTEMS 1. General This section describes the Indicating/Recording Systems
USAF Aero Club T-41B (Cessna R-172E) Aircraft Exam Updated February 2017
USAF Aero Club T-41B (Cessna R-172E) Aircraft Exam Updated February 2017 Instructions Complete the supplement following exam using the answer sheet provided. Do not assume information not specifically
ITEMS INCLUDED. 2.4GHz Controller
READ THESE INSTRUCTIONS BEFORE FLYING! ITEMS INCLUDED.4GHz Controller Flight Battery Charger SKY Cruiser LiPo Flight Battery AA Batteries AC Power Supply WARNINGS FOR YOUR SAFETY PLEASE READ AND UNDERSTAND
Compiled by Matt Zagoren
The information provided in this document is to be used during simulated flight only and is not intended to be used in real life. Attention VA's - you may post this file on your site for download. Please
ADTS542F. Your touch, our technology. Wireless ADTS500 Series Easy-to-Use Pitot Static Tester. Features
GE ADTS542F Wireless ADTS500 Series Easy-to-Use Pitot Static Tester Features ADTS Touch hand terminal with Bluetooth wireless technology (backup cable supplied) Swipe action, touch screen user interface
Dassault Falcon 50 Microsoft Flight Simulator 2004
Dassault Falcon 50 Microsoft Flight Simulator 2004 Model and bitmaps Yannick Lavigne Custom gauge programming Fred Banting Flight dynamics Rob Young and Eric Dantes. Foto: Gerry Stegmeier Foto: Dassault
ADTS542F. Your touch, our technology. GE Oil & Gas. Wireless ADTS500 Series Easy-to-Use Pitot Static Tester. Features
GE Oil & Gas ADTS542F Wireless ADTS500 Series Easy-to-Use Pitot Static Tester Features ADTS Touch hand terminal with WiFi and Bluetooth wireless technology (backup cable supplied) Swipe action, touch screen
DUCHESS BE-76 AND COMMERCIAL MULTI ADD-ON ORAL REVIEW FOR CHECKRIDE
DUCHESS BE-76 AND COMMERCIAL MULTI ADD-ON ORAL REVIEW FOR CHECKRIDE The Critical Engine The critical engine is the engine whose failure would most adversely affect the airplane s performance or handling
F135 Propulsion Integration Topics for Symposium on Jet Engines Haifa, Israel
F135 Propulsion Integration Topics for Symposium on Jet Engines Haifa, Israel Tom Johnson Program Chief Engineer Operational Military Engines 25 October 2012 J6924_F135_Propulsion_2012-1 Agenda F135 Development
Flight Testing of Your Europa Equipped with the Airmaster Propeller By Bud Yerly Custom Flight Creations, Inc.
Flight Testing of Your Europa Equipped with the Airmaster Propeller By Bud Yerly Custom Flight Creations, Inc. Once you've selected the desired blade and hub for your Airmaster constant speed propeller,
Cessna 172RG WARNING. Maximum Demonstrated Crosswind. Takeoff or landing..15 KTS
Cessna 172RG INTRODUCTION: This aircraft checklist contains information from the original manufacturer s Pilot Information Manual. Normal procedures associated with optional systems can be found in Section
AIAA Undergraduate Team Aircraft Design
Homeland Defense Interceptor (HDI) 2005 2006 AIAA Undergraduate Team Aircraft Design Group Members and Responsibilities Name Discipline AIAA Number John Borgie Configuration and Systems 268357 Ron Cook
Appenidix E: Freewing MAE UAV analysis
Appenidix E: Freewing MAE UAV analysis The vehicle summary is presented in the form of plots and descriptive text. Two alternative mission altitudes were analyzed and both meet the desired mission duration.
Contents. BAE SYSTEMS PROPRIETARY Internal UNCLASSIFIED Use Only Unpublished Work Copyright 2013 BAE Systems. All rights reserved.
Contents Aim of presentation. Who do we interface with. What does safe separation entail. What do we class as a store. Why is there a need for safe separation analysis. Methods for performing safe separation
Design Considerations for Stability: Civil Aircraft
Design Considerations for Stability: Civil Aircraft From the discussion on aircraft behavior in a small disturbance, it is clear that both aircraft geometry and mass distribution are important in the design
Electronics International inc.
Electronics International inc. MVP-50T Marking and Configuration Requirements Rev B: 6/24/11 Electronics International Inc. will configure the MVP-50T to the range limits, markings and hardware outlined
Highly Augmented Flight Controls
Part 23 Advanced Flight Path Control Certification Federal Aviation Administration Highly Augmented Flight Controls Presentation to: Prepared by: Date: Oct 21, 2015 On Demand Mobility Workshop Dave Sizoo
COMPARISON OF FIXED AND CS PROPELLER PERFORMANCE. Procedure
High Performance Propeller Systems Airmaster Propellers Ltd 20 Haszard Rd, Massey PO Box 374, Kumeu Auckland, New Zealand Ph: +64 9 833 1794 Fax: +64 9 833 1796 Email: sales@propellor.com Web: www.propellor.com
ADVENT. Aim : To Develop advanced numerical tools and apply them to optimisation problems in engineering. L. F. Gonzalez. University of Sydney
ADVENT ADVanced EvolutioN Team University of Sydney L. F. Gonzalez E. J. Whitney K. Srinivas Aim : To Develop advanced numerical tools and apply them to optimisation problems in engineering. 1 2 Outline
FLIGHT HANDLING NOTES CHECK LIST & PERFORMANCE DATA GROB G 109B G-KNEK
FLIGHT HANDLING NOTES CHECK LIST & PERFORMANCE DATA GROB G 109B G-KNEK Before Starting Engine PREFLIGHT CHECK COMPLETED. 1. Adjust pedals and back rests 2. Adjust and secure seat harness 3. Folding doors
Table of Contents Aircraft... 4
Strike Fighters Table of Contents Aircraft... 4 Compared Statistics... 4 Mission Performances... 5 Size... 6 Load... 7 Fuel... 7 Systems... 8 Weapons... 9 AIM-9X... 9 AIM-7M... 9 AIM-54C... 10 AIM-120D...
2. What type and size (hp) engine does the airplane have? Lycoming O540-JC35D rated at 235 BHP at 2400 RPM
This quiz will help test your knowledge of the POH and the systems and equipment in CR-182 N133BW. In preparation for your checkout flight, answer all of the following questions as thoroughly as possible
OPTIMAL MISSION ANALYSIS ACCOUNTING FOR ENGINE AGING AND EMISSIONS
OPTIMAL MISSION ANALYSIS ACCOUNTING FOR ENGINE AGING AND EMISSIONS M. Kelaidis, N. Aretakis, A. Tsalavoutas, K. Mathioudakis Laboratory of Thermal Turbomachines National Technical University of Athens
Fuel Efficiency The Industry, IATA and You
Fuel Efficiency The Industry, IATA and You Captain Pat Jordan Airline Cost Conference The Industry Airline Cost Conference Still high fuel price Industry Challenges Fuel represents 32% of airline budget
ACTIVE STICK & THROTTLE FOR F-35. Joseph Krumenacker NAVAIR Flight Controls / JSF Vehicle Systems 16 October 2008
ACTIVE STICK & THROTTLE FOR F-35 Joseph Krumenacker NAVAIR Flight Controls / JSF Vehicle Systems 16 October 2008 Intro Joe Krumenacker holds a BS in Aerospace & Mechanical Engineering from the University
Type Acceptance Report
TAR 17/21B/13 IAE PW1100G-JM/PW1400G-JM Series Aircraft Certification Unit TABLE OF CONTENTS EXECUTIVE SUMMARY 1 1. INTRODUCTION 1 2. PRODUCT CERTIFICATION DETAILS 1 4. NZCAR 21.43 DATA REQUIREMENTS 3
N2040P 35 Bonanza IO-520 EDM-930
N2040P 35 Bonanza IO-520 EDM-930 Includes 78 flights between Jul 06, 2014 and Jul 05, 2016, compared with 2596 flights by a cohort of 107 35 Bonanza aircraft. PERCENT POWER IN CRUISE Measures your engine's
D e d i c a t e d t o h e l p i n g b u s i n e s s a c h i e v e i t s h i g h e s t g o a l s NBAA Light Business Airplane Buyer s Guide
D e d i c a t e d t o h e l p i n g b u s i n e s s a c h i e v e i t s h i g h e s t g o a l s. 2010 NBAA Light Business Airplane Buyer s Guide Introduction How to Begin Planning a Light Business Airplane
CESSNA P 337 H Pressurized Skymaster
CESSNA P 337 H Pressurized Skymaster N777SN Quick reference training guide This training manual cannot be used as a substitute for the official pilots operating handbook. Page 1 - 1. Take off (normal)
Elmendorf Aero Club Aircraft Test
DO NOT WRITE ON THIS TEST JAN 2014 Elmendorf Aero Club Aircraft Test SENECA II For the following questions, you will need to refer to the Pilots Information Manual for the PA-34-200T. USE ANSWER SHEET
AIRCRAFT ACCIDENT AND INCIDENT INVESTIGATION DIVISION
FUEL EXHAUSTION MANAGEMENT SAFETY ARTICLE This report will consider the two main reasons why fuel stops getting to an engine during flight. Fuel exhaustion happens when there is no useable fuel remaining
Australian Government
Australian Government Civil Aviation Safety Authority PPL & CPL (Aeroplane) Workbook Version 1-1 September 214 The Civil Aviation Safety Authority (CASA) owns copyright of this workbook. The workbook is
DASSAULT AVIATION Proprietary Data
F900EX EASY 02-27-00 CODDE 1 PAGE 1 / 2 TABLE OF CONTENTS 02-27 02-27-00 TABLE OF CONTENTS 02-27-05 GENERAL Introduction Flight control sources Primary and secondary flight controls 02-27-10 DESCRIPTION
For public dissemination IATA Super-absorbent Polymer (SAP) Special Interest Group Data summary and proposed roadmap
IATA Super-absorbent Polymer (SAP) Special Interest Group Data summary and proposed roadmap On 14 November 2017 the IATA SAP Special Interest Group released the statement shown in Appendix A. This paper
Early Flights Achievement with the Aermacchi M-346 Advanced Trainer
Paolo Chimetto & Rodolfo Carabelli Aermacchi M-346 Flight Test Aermacchi S.p.A. Via Paolo Foresio 1 21040 Venegono Superiore (Varese) Italy Telephone 0039 331 813 965 FAX 0039 331 813 042 chimetto.paolo@aermacchi.it
Proposed Special Condition C-xx on Rudder Control Reversal Load Conditions. Applicable to Large Aeroplane category. Issue 1
Proposed Special Condition C-xx on Rudder Control Reversal Load Conditions Introductory note: Applicable to Large Aeroplane category Issue 1 The following Special Condition has been classified as an important
The cockpit. UFCD Upfront control display. Head up display. Right DDI - Digital display indicator. Left DDI - Digital display indicator
Super Hornet The cockpit Head up display Left DDI - Digital display indicator Fuel gauge / engine gauge Landing gear lever UFCD Upfront control display Right DDI - Digital display indicator HUD settings
Test of. Bell UH-1Y Venom. Produced by Area-51 Simulations
Test of Bell UH-1Y Venom Produced by Area-51 Simulations The Bell UH-1Y Venom is a twin-engine, medium size utility helicopter featuring a four bladed rotor, upgraded avionic and a glass cockpit from its