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12 Nomenclature Mission D mission segment distance dR mission segment range contribution E endurance R range T mission segment time ˙w fuel flow Environment cs speed of sound g gravitational acceleration h altitude T temperature, ◦Ror◦K Vw wind speed μ viscosity ν kinematic viscosity ρ density τ temperature, ◦For◦C Axis Systems A component aerodynamic B component F aircraft I inertial V velocity Geometry ℓ length L reference length (fuselage length, rotor radius, or wing span) Swet wetted area SL, BL, WL fixed input position (station line, buttline, waterline) positive aft, right, up; arbitrary origin x/L, y/L, z/L scaled input position; positive aft, right, up; origin at reference point x, y, z calculated position, aircraft axes; positive forward, right, down; origin at reference point for geometry, origin at center of gravity for motion and loads zF component position vector, in aircraft axes, relative reference point
Nomenclature 13 Motion aF AC aircraft linear acceleration n load factor V aircraft velocity magnitude vF AC aircraft velocity Vc Vcal climb velocity calibrated airspeed, V ρ/ρ0 Vf forward velocity Vh horizontal velocity Vs sideward velocity φF , θF , ψF roll, pitch, yaw angles; orientation airframe axes F relative inertial axes θV , ψV ˙ψF climb, sideslip angles; orientation velocity axes V relative inertial axes turn rate aircraft angular velocity ω F AC Aerodynamics and Loads cd, cℓ section drag, lift coefficients CD, CY , CL component drag, side, lift force coefficients Cℓ, CM, CN component roll, pitch, yaw moment coefficients D, Y , L aerodynamic drag, side, lift forces (component aerodynamic axes A) D/q drag area, SCD (S = Reference area of component) F force ℓf ratio flap chord to airfoil chord, cf /c M moment Mx, My, Mz aerodynamic roll, pitch, yaw moments (component aerodynamic axes A) q dynamic pressure, 1/2ρ|v| 2 v component velocity relative air (including interference) α angle of attack, component axes B relative aerodynamic axes A β sideslip angle, component axes B relative aerodynamic axes A flap deflection δf Aircraft Aref reference rotor area, fAA; typically projected area of lifting rotors c component control, c = STcAC + c0 cAC aircraft control De aircraft effective drag, P/V DL disk loading, WD/Aref L/De M aircraft effective lift-to-drag ratio, WV/P aircraft hover figure of merit, W Sref W/2ρAref/P reference wing area, S; sum area all wings T control matrix WL wing loading, WD/Sref tilt control variable αtilt
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 and 22: Chapter 2 Nomenclature The nomencla
Page 23: Nomenclature 11 Fuel Tanks Power Na
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
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Aircraft 63 disk area); or the drag
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Aircraft 65 7-10 Performance Indice
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Aircraft 67 WEIGHT EMPTY STRUCTURE
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Chapter 8 Systems The systems compo
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Chapter 9 Fuselage There is one fus
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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
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Rotor 79 propulsion group. The driv
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Rotor 81 plane command. The collect
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Rotor 83 or just CSF = WCHF with no
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Rotor 85 If μ is zero, the equatio
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Rotor 87 The velocity ratio is fW =
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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
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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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Chapter 19 AFDD Weight Models This
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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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