2018/3/11 Wing group-flap mass 国上清庆大坐 Tail Group 国上清大学 The flap mass can be estimated by The tail mass can be estimated by MT Mn My Suk +Syky l mass Area of Fin Rudder 115 115 130D0 Notes: Values for ku and ky ranges from 22-32 kg/m",typical values are ku=25. k=28kg/m Mass of Nacelle,Landing Gear 国上活大坐 Propulsion group 国上清支大峰 Nacelle mass can be estimated by 6.8-T (T<6O0W) or 丛=12%022% 2760+2.2-T(T>600kW) 1.43-M。 (M.<10000kg) 1.16M.+2700 (M.>10000kg) Symbol Description MyNacele mass In which, =87+.4-BPR TTotal Statk Engine Thrust Landing gear mass Symbol Descrlption M Engine bare mass Muc [4.45%(Existing Breaks) TEngine Static Thrust .35%(Modern Breaks) BPR Bypass Ratlo Surface controls(movable surfaceson the wing not included in the flaps) Mg=0.4-M% Notes Notes: c52017.2018 Fixed Equipment and Operational Items 国上清大学 Fuel Tank Volume 图上活大坐 Fixed equipment includes flight control systems and furnishings 14% Short-Haul Volume=o.33L[S,+Sz+o.5(S,+S,)l Mediio-Haul 8% Long-Haul Operational Items incude Base area S, Crew provisions including maps and flight manuals-okg Cammuter Service 045 Short-range service 0.68 Base area S2 snack-ocly Service. 227 Medium -range servoe 1.36 Medium-Ranre Servce6 25 Long-月ange Ser1ce 25 b. LonE-Range Service 862 M o.151 058 mbol Over-water&extended capaory (r) 22018/3/11 2 © Shanghai Jiao Tong University – Dr. Wenbin Song School of Aeronautics and Astronautics, 2017-2018 Wing group – flap mass   0.75 2 0.1875 / 0.0002 sin( ) 2.706                 FLAP appro FLAND FLAP FLAP FLAP FLAP FLAP t c V D M K S B S The flap mass can be estimated by KFLAP 1.0 Single slot 1.15 Double slot 1.15 Single slot + Fowler 1.30 Double slot + Fowler © Shanghai Jiao Tong University – Dr. Wenbin Song School of Aeronautics and Astronautics, 2017-2018 Tail Group Symbol Description MT Tail mass MH Mass of Tailplane + Elevator MV Mass of Fin + Rudder SH Area of Tailplane + elevator SV Area of Fin + Rudder kH Statistical Densities kV T H V H H V V M  M  M  S  k  S  k The tail mass can be estimated by Notes: Values for kH and kV ranges from 22-32 kg/m2 , typical values are kH=25, kV =28kg/m2 © Shanghai Jiao Tong University – Dr. Wenbin Song School of Aeronautics and Astronautics, 2017-2018 Mass of Nacelle, Landing Gear Symbol Description MN Nacelle mass T Total Static Engine Thrust          2760 2.2 ( 600 ) 6.8 ( 600 ) T T kN T T kN M N Nacelle mass can be estimated by 1.2% to 2.2% M M TO N or  Landing gear mass     4.35% ( ) 4.45% ( ) Modern Breaks Existing Breaks M M TO UC Surface controls (movable surfaces on the wing not included in the flaps) 0.684 0.4 MSC MTO   Notes: 1. can be reduced by 25% for a simple control system without leading edge device Msc © Shanghai Jiao Tong University – Dr. Wenbin Song School of Aeronautics and Astronautics, 2017-2018 Propulsion group Symbol Description Me Engine bare mass T Engine Static Thrust BPR Bypass Ratio The mass of engine group, including engine, reverse bucket, systems, can be estimated by BPR T Me  8.7 1.14          1.16 2700 ( 10000 ) 1.43 ( 10000 ) M M kg M M kg M e e e e PROP In which, Notes: 1. Multiply by 1.08 if the aircraft has high wings and wing mounted undercarriages © Shanghai Jiao Tong University – Dr. Wenbin Song School of Aeronautics and Astronautics, 2017-2018 Fixed Equipment and Operational Items Fixed equipment includes flight control systems and furnishings          Long Haul Medium Haul Short Haul M M TO FE 8% 11% 14% Operational Items include Crew provisions including maps and flight manuals – 10kg 3 2 MROF  0.151V Commuter Service 0.45 Snack – only Service 2.27 Medium – Range Service 6.25 Long – Range Service 8.62 Cabin supplies per passenger, add 2.27kg for first class passenger Short – range service 0.68 Medium – range service 1.36 Long – Range Service 2.95 Water and toilet provision per passenger Short over land 0.68 Over-water & extended flights 1.36 Safety equipment per passenger Symbol Description MROF Residual Oil and Fuel Mass V Fuel capacity (ltr) Residual oil and fuel © Shanghai Jiao Tong University – Dr. Wenbin Song School of Aeronautics and Astronautics, 2017-2018 Fuel Tank Volume Volume=0.33L[S1+S2+0.5(S1 + S2 )] L b1a1 b2 a2 Base area S1 Base area S2