A project supported by AIRBUS and the CAAC Date of the module • Table of contents • Flight operations duties • European Applicable Regulation • General • General aircraft limitations • Payload Range • Operating limitations • In flight performance • One engine inoperative performance • Flight planning • weight and balance A project supported by AIRBUS and the CAAC Date of the module 1 - International standard atmosphere 2 - Altimetry principle 3 - Operating speeds 4 - Flight mechanics Table of Contents A project supported by AIRBUS and the CAAC Date of the module 1 - International standard atmosphere 2 - Altimetry principle 3 - Operating speeds 4 - Flight mechanics Table of Contents A project supported by AIRBUS and the CAAC Date of the module -60 -40 -20 0 20 40 60 2 4 6 8 10 12 Altitude Sea level TROPOSPHERE TROPOPAUSE STRATOSPHERE -56.5°C 15°C Temperature (°C) (km) 5000 10000 15000 20000 25000 30000 35000 40000 (ft) subsonic jet transport cruise level International Standard Atmosphere A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module International Standard Atmosphere pressure altitude (Zp) 500 850 1013.25 Ps 200 250 300 (hPa) Zp = f(P) ISA table 2 4 6 8 10 12 5000 10000 15000 20000 25000 30000 35000 40000 (ft) (km) A project supported by AIRBUS and the CAAC Date of the module 1 - International standard atmosphere 2 - Altimetry principle 3 - Operating speeds 4 - Flight mechanics Table of Contents A project supported by AIRBUS and the CAAC Date of the module Zi Zpamb Zpset Zp pressure altitude 0 Pamb Pset 1013.25 (hPa) Ps Zp = f(Ps) ISA Table Altimetry principle A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module Altimeter function on PFD A project supported by AIRBUS and the CAAC Date of the module Standard setting: 1013.25 hPa QNH setting QFE setting Radio height (AAL) Height Altitude Flight Level QNH QFE 1013 Altimeter setting A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module QNH 1013 hPa sea level descent approach 1013 1013 take-off climb QNH QNH Altimeter setting Transition altitude Transition level A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module Zi (QNH) Za ISA ISA + 30° ISA - 30° Temperature effect on true altitude A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module 1013 STD + Za > Zi 1013 STD Za = Zi 1013 STD - Za < Zi Temperature effect on true altitude A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module OM Za = cst STD + STD STD - Zi = Za Zi < Za Zi > Za Temperature effect on the altimeter indication A project supported by AIRBUS and the CAAC Date of the module 1 - International standard atmosphere 2 - Altimetry principle 3 - Operating speeds 4 - Flight mechanics Table of Contents A project supported by AIRBUS and the CAAC Date of the module Impact pressure pick-off (Stby + Capt.) F/O on the other side Static ports (Stby + F/O + Capt.) symmetrical on the other side, to avoid yaw errors Pitot and static probes A project supported by AIRBUS and the CAAC Date of the module P0 Pi P0 Dynamic: = Pi - PS Static: PS Air flow: V Impact pressure pick-off: Pi Static port Vi Speed measurement A project supported by AIRBUS and the CAAC Date of the module Wind TAS GS DA GS = Ground Speed DA = Drift Angle TAS = True Air Speed Ground speed and drift angle A project supported by AIRBUS and the CAAC Date of the module A project supported by AIRBUS and the CAAC Date of the module Speed conversion summary DENSITY CORRECTION = 120 TAS = 445 kt COMPRESSIBILITY CORRECTION = -10 kt POSITION ERROR CORRECTION = +2 kt CAS = 335 kt IAS = 333 kt FL 200 IAS = 333 kt POSITION ERROR CORRECTION = -1 kt TAS = CAS = 332 kt SEA LEVEL Air speed (kt) 250 300 350 400 450 Altitude A project supported by AIRBUS and the CAAC Date of the module True Air Speed variation 300 / 0.78 climb 200 250 300 350 400 450 500 50 100 150 200 250 300 350 400 450 tropopause iso CAS 300 FL TAS (kt) iso Mach 0.78 A project supported by AIRBUS and the CAAC Date of the module when thrust = drag level flight when thrust < drag descent when thrust > drag climb Thrust and drag A project supported by AIRBUS and the CAAC Date of the module 1 - International standard atmosphere 2 - Altimetry principle 3 - Operating speeds 4 - Flight mechanics Table of Contents A project supported by AIRBUS and the CAAC Date of the module Balance of forces for steady level flight at constant speed lift thrust weight = mg drag lift = weight thrust = drag A project supported by AIRBUS and the CAAC Date of the module Lift equation : Weight = ½ S (TAS)2 CL Drag equation : Thrust = ½ S (TAS)2 CD Power equation : Power = Thrust × TAS = ½ S (TAS)3 CD A project supported by AIRBUS and the CAAC Date of the module As a function of Mach number : Weight = 0.7 S PS M2 CL Thrust = 0.7 S PS M2 CD As a function of P0 : the pressure ratio = PS/P0 is introduced (P0 pressure at ZP = 0) : Weight / = 0.7 S P0 M2 CL Thrust / = 0.7 S P0 M2 CD A project supported by AIRBUS and the CAAC Date of the module Balance of forces in climb Gza TAS Gx Gxa W= mg Gz L T D ground datum line aerodynamics datum line aircraft datum line : climb angle : angle of attack flight attitude A project supported by AIRBUS and the CAAC Date of the module angle of attack climb angle climb Thrust climb angle TAS flight attitude TAS TAS Rate of climb (RC) Climb Angle and Rate of Climb Angle of attack Thrust 0 climb angle RC = TAS sin A project supported by AIRBUS and the CAAC Date of the module Longitudinal axis : Thrust = Drag + weight sin Vertical axis : Lift = Weight cos if is small sin tan cos 1 Thrust = Drag + Weight Lift = Weight = Thrust - Drag Weight A project supported by AIRBUS and the CAAC Date of the module Thrust as a function of speed D,T Speed thrust drag Given m, t°C, Zp, thrust lever position A project supported by AIRBUS and the CAAC Date of the module Expression of the climb angle : Expression of the rate of climb RC = TAS . = 100 Thrust Weight 1 L/D RC (ft/mn) TAS (kt) . (%) A project supported by AIRBUS and the CAAC Date of the module Balance of forces in descent TAS Gx Gxa Gza Gz L W= mg T D ground datum line aerodynamics datum line aircraft datum line : descent angle : angle of attack flight attitude A project supported by AIRBUS and the CAAC Date of the module Gradient of descent : if Thrust 0 (Idle) Rate of descent : = Thrust - Drag Weight < 0 = - 100 1 L/D RC (ft/mn) TAS (kt) . (%) A project supported by AIRBUS and the CAAC Date of the module D/ M increasing W/ D/as a function of Mach number A project supported by AIRBUS and the CAAC Date of the module gradient D,T Speed thrust drag climb Speed max L/Dmax Given m, t°C, Zp cruise speed climb speeds Climb gradient versus speed Climb gradient is maximum when the Drag is minimum or L/D maximum作者: 忙盲忙 时间: 2010-7-28 08:55:49 标题: 楼主辛苦啦！
楼主辛苦啦！作者: 凌晨一点 时间: 2010-7-31 15:49:46
辛苦啦楼主作者: f214216709 时间: 2010-8-2 13:52:42
飞行气象？作者: 21372770 时间: 2010-8-16 17:10:04
check it out作者: 胖子 时间: 2010-9-2 00:02:15
非常感谢
作者: wangchen 时间: 2010-9-2 11:58:08
接收新回复邮件通知作者: gjsx 时间: 2010-9-9 07:55:28
A project supported by AIRBUS and the CAAC作者: desperado 时间: 2010-9-9 15:22:49
桂林民航气象预报的现状作者: wwjkankan 时间: 2010-9-11 09:56:41
多谢，收藏之作者: cdzfk 时间: 2010-9-17 10:54:07
谢谢分享了，好东西作者: puffyandjil 时间: 2010-10-28 16:05:25
作者: ida51737 时间: 2010-11-4 15:13:38
upup nice
upup作者: s22780 时间: 2010-11-4 19:47:51
I’M LYING ON THE BED作者: gjsx 时间: 2010-11-12 08:11:34
-
Zi = Za
Zi < Za Zi > Za
Temperature effect on the altimeter indication
A project supported by AIRBUS and the CAAC
Date of the module
1 - International standard atmosphere作者: show616 时间: 2011-3-17 13:49:18
= Pi - PS Static: PS
谢谢分享