Completed notes of the course

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Airplane performance and dynamics Glossary - E : LIFT TO ☐RA0 RATIO • ]i ANGLE OF CLIMB • V0 : RATE OF CLIMB . VV : POWER LOADING Pb i W ' ' WING LOADING s ' J : DENSITY RATIO INTRODUCTIONTOTHEAIRCRAFT DESIGN • MAIN PHASESOFTHEDESIGN PROCESS: 1)CONCEPTUAL DESIGN GENERAL CONFIGURATION OF THEAIRCRAFT (ARCHITECTURE ) INITIAL SIZING : MT0W Pb(POWEROFSHAFT) T /THRUST) 5/WINGSURFACE: IT INCLUDESTHESECTIONOFTHEFUSELAGE) - s 2)PRELIMINARY DESIGN 3)EXECUTIVE DESIGN MISSION REQUIREMENTS 1)PERFORMANCE SPEEDS STALLING SPEED: MINIMUM SPEED WHICHALLOWS TO STAY ONFLIGHT MAXIMUMSPEED BEST RANGE ECONOMIC SPEEDS : BEST ENDURANCE MAXRATEOFCLIMB MANEUVERINGSPEED a-- RANGE ENDURANCE TIME TO CLIMB TAKE OFF DISTANCE LANDING DISTANCE 2)PAYLOAD 3)PRESSURIZATION ' IT IS CONSIDERED IN MISSION REQS BECAUSE IT ALLOWS TO FLIGHT OVER A CERTAIN ItEIGHT MISSION PROFILE 'T0D T0C . CRUISE .LOITER T0C: TOPOF CLIMB aTAXI . LND. . T0Di TOPOF ☐C-SENT A B C DIVERSION • DIVERSION: IT'STHEB-PLAN WHEN THEPILOTCAN'TLAND IN B • THIS SCHEME ALLOWS TO ATTACH FOR EVERY PHASE ITS MISSION REQUIREMENTS: BR: BESTRANGECONDITION MINIMUMFUELCONSUMPTION . . RD: RATEOF DESCENT TIPICALLYLINKED TO THE PRESSURIZATIONOF ⑥ " ""£°" " ""° ""£ &"" AC: ANGLEOFCLIMB . BEi BESTENDURANCE ' . I r A B PUNTUALPERFORMANCES DRAG POLAR CL ((MAX - EMAX. E: = LIFT TO DRAGRATIO [DM1N ' I CD0 CD PENAULDDIAGRAMS D - min (D) ✓STALL ✓ Pr tgO= Pr=D - V min /Pr) . . thinkVminD V✓STALL VmaxfVmaxE ANALYTICALPOLAR CL . - - . i- a CD [☐= [☐☐+ KCLZ i.. . . CL E= CL MaxE = minD CDE.MAX. . FMAX F= ECL MaxF= minPr (°"" G= E max 6= minD <☐☐ " ZCDOGCDO [☐ (L ✓ §CD0