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10 Nomenclature Acronyms AFDD U.S. Army Aeroflightdynamics Directorate ASM available seat mile CAS calibrated airspeed CPI consumer price index CRP contingency rated power DoD Department of Defense ECU environment control unit EG engine group ERP emergency rated power FCE flight control electronics ICAO International Civil Aviation Organization IGE in-ground-effect IRP intermediate rated power IRS infrared suppressor ISA International Standard Atmosphere ISO International Organization for Standardization JVX Joint Vertical Experimental MCP maximum continuous power MEP mission equipment package MRP maximum rated power OEI one-engine inoperative OGE out-of-ground-effect PG propulsion group RPTEM referred parameter turboshaft engine model SDGW structural design gross weight SLS sea-level, standard day TAS true airspeed WMTO maximum takeoff weight Weights WD design gross weight WE empty weight WMTO maximum takeoff weight WSD structural design gross weight WG gross weight, WG = WE + WUL = WO + Wpay + Wfuel WO operating weight, WO = WE + WFUL WUL useful load, WUL = WFUL + Wpay + Wfuel Wpay payload Wfuel fuel weight WFUL fixed useful load Wburn mission fuel burn Wvib vibration control weight Wcont contingency weight χ technology factor
Nomenclature 11 Fuel Tanks Power Nauxtank Vfuel−cap Waux−cap Wfuel−cap Ninop PavP G PavEG PreqPG PreqEG Pcomp Pxmsn Pacc PDSlimit PESlimit PRSlimit number of auxiliary fuel tanks fuel capacity, volume auxiliary-fuel-tank capacity fuel capacity, maximum usable fuel weight number of inoperative engines, engine group power available, propulsion group; min( fP PavEG, (Ωprim/Ωref)PDSlimit) power available, engine group; (Neng − Ninop)Pav power required, propulsion group; Pcomp + Pxmsn + Pacc power required, engine group component power required transmission losses accessory power drive-system torque limit (specified as power limit at reference rotor speed) engine-shaft rating rotor-shaft rating Engine Daux momentum drag FN net jet thrust ˙m mass flow (conventional units) N specification turbine speed Neng number of engines in engine group (EG) Peng sea-level static power available per engine at specified takeoff rating Pav power available, installed; min(Pa − Ploss,Pmech) Pa power available, uninstalled Preq power required, installed; Pq − Ploss Pq power required, uninstalled Ploss installation losses Pmech mechanical power limit sfc specific fuel consumption, ˙w/P (conventional units) SP specific power, P/ ˙m (conventional units) SW specific weight, P/W ˙w fuel flow (conventional units) Tip Speed and Rotation specification engine-turbine speed (rpm) Nspec r gear ratio; Ωdep/Ωprim for rotor, Ωspec/Ωprim for engine Vtip−ref Ωprim Ωdep Ωspec reference tip speed, propulsion group primary rotor; each drive state primary-rotor rotational speed, Ω=Vtip−ref/R dependent-rotor rotational speed, Ω=Vtip−ref/R specification engine-turbine speed
Page 1 and 2: NASA/TP-2009-215402 NDARC NASA Desi
Page 3 and 4: NASA/TP-2009-215402 NDARC NASA Desi
Page 5 and 6: TABLE OF CONTENTS CHAPTER 1 - INTRO
Page 7: TABLE OF CONTENTS (cont.) CHAPTER 1
Page 10 and 11: viii LIST OF FIGURES (cont.) Figure
Page 13 and 14: Chapter 1 Introduction The NASA Des
Page 15 and 16: Introduction 3 of rotorcraft config
Page 17 and 18: Introduction 5 previous case DESIGN
Page 19 and 20: Introduction 7 4) Scully, M.; and F
Page 21: Chapter 2 Nomenclature The nomencla
Page 25 and 26: Nomenclature 13 Motion aF AC aircra
Page 27 and 28: Chapter 3 Tasks The NDARC code perf
Page 29 and 30: Tasks 17 engine group is found (inc
Page 31 and 32: Tasks 19 3-4 Maps 3-4.1 Engine Perf
Page 33 and 34: Chapter 4 Operation 4-1 Flight Cond
Page 35 and 36: Operation 23 e) Input payload weigh
Page 37 and 38: Operation 25 Table 4-1. Mission seg
Page 39 and 40: Operation 27 horizontal ground dist
Page 41 and 42: Operation 29 climb for zero power m
Page 43 and 44: Operation 31 a) Horizontal velocity
Page 45 and 46: Operation 33 From the pressure p =
Page 47 and 48: Chapter 5 Solution Procedures The N
Page 49 and 50: Solution Procedures 37 Sizing Task
Page 51 and 52: Solution Procedures 39 relaxation i
Page 53 and 54: Solution Procedures 41 Table 5-4. T
Page 55 and 56: Solution Procedures 43 successive s
Page 57 and 58: Solution Procedures 45 initialize e
Page 59 and 60: Chapter 6 Cost Costs are estimated
Page 61 and 62: Cost 49 Table 6-1. DoD and CPI infl
Page 63 and 64: Cost 51 predicted base price (1994$
Page 65 and 66: Chapter 7 Aircraft The aircraft con
Page 67 and 68: Aircraft 55 The tilt control variab
Page 69 and 70: Aircraft 57 forward axes for descri
Page 71 and 72: Aircraft 59 For steady-state flight
Page 73 and 74:
Aircraft 61 where Δz F = z F − z
Page 75 and 76:
Aircraft 63 disk area); or the drag
Page 77 and 78:
Aircraft 65 7-10 Performance Indice
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Aircraft 67 WEIGHT EMPTY STRUCTURE
Page 81 and 82:
Chapter 8 Systems The systems compo
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Chapter 9 Fuselage There is one fus
Page 85 and 86:
Fuselage 73 αe = αfus − αzl, w
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Chapter 10 Landing Gear There is on
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Chapter 11 Rotor The aircraft can h
Page 91 and 92:
Rotor 79 propulsion group. The driv
Page 93 and 94:
Rotor 81 plane command. The collect
Page 95 and 96:
Rotor 83 or just CSF = WCHF with no
Page 97 and 98:
Rotor 85 If μ is zero, the equatio
Page 99 and 100:
Rotor 87 The velocity ratio is fW =
Page 101 and 102:
Rotor 89 T/T ∞ 1.3 1.2 1.1 1.0 Ha
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Rotor 91 TPP tilt / cyclic magnitud
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Rotor 93 with an average over the r
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Rotor 95 (all equal to 1 for μz =0
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Rotor 97 κ 1.30 1.25 1.20 1.15 1.1
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Rotor 99 (C T /σ) s c d mean 0.20
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Rotor 101 11-5.1.3 Twin Rotors For
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Rotor 103 The wake is a skewed cyli
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Rotor 105 weight per lifting rotor;
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Chapter 12 Force The force componen
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Chapter 13 Wing The aircraft can ha
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Wing 111 denotes outboard edge, sub
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Wing 113 13-3.1 Lift The wing lift
Page 127 and 128:
Wing 115 The wing interference at t
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Chapter 14 Empennage The aircraft c
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Empennage 119 14-4 Weights The tail
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Chapter 15 Fuel Tank 15-1 Fuel Capa
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Fuel Tank 123 if Wfuel >Wfuel−max
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Chapter 16 Propulsion The propulsio
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Propulsion 127 If the sum of the fi
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Chapter 17 Engine Group The engine
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Engine Group 131 The engine group p
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Engine Group 133 specific fuel cons
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Chapter 18 Referred Parameter Turbo
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Referred Parameter Turboshaft Engin
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Page 155 and 156:
Page 157 and 158:
Page 159 and 160:
Chapter 19 AFDD Weight Models This
Page 161 and 162:
AFDD Weight Models 149 The spar-cap
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AFDD Weight Models 151 19-1.2 Aircr
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AFDD Weight Models 153 where w = nz
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AFDD Weight Models 155 units as use
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AFDD Weight Models 157 Table 19-9.
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AFDD Weight Models 159 where fP = f
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AFDD Weight Models 161 The conversi
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AFDD Weight Models 163 19-12 Foldin
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AFDD Weight Models 165 error (%) er
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