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108 Force 12–2 Performance and Weights The force generation requires a fuel flow that is calculated from an input thrust-specific fuel consumption (sfc): ˙w = A(sfc). Units of sfc are pound/hour/pound, or kilogram/hour/Newton. The force component weight is identified as either engine-system or propeller/fan installation weight, both of the propulsion group. The force component weight is calculated from specific weight and the design maximum force Fmax, plus a fixed increment: W = SFmax +ΔW .
Chapter 13 Wing The aircraft can have one or more wings, or no wings. 13–1 Geometry The wing is described by planform area S, span b, mean chord c = S/b, and aspect ratio AR = b 2 /S. These parameters are for the entire wing. The geometry is specified in terms of two of the following parameters: S or wing loading W/S, b (perhaps calculated from other geometry), c, AR = b 2 /S. With more than one wing, the wing loading is obtained from an input fraction of design gross weight, W = fW WD. Optionally the span can be calculated from a specified ratio to the span of another wing. Optionally for the tiltrotor configuration, the wing span can be calculated from the fuselage and rotor geometry: b =2(fR+ dfus)+wfus, where R is the rotor radius (cruise value for variable-diameter rotor), dfus the rotor-fuselage clearance, and wfus the fuselage width. Note that the corresponding option for the rotor-hub position is yhub = ±(fR+ dfus + 1/2wfus). Optionally the wing span can be calculated from the rotor-hub position: b =2|yhub| (regardless of how the rotor position is determined). As implemented, symmetry is not assumed; rather the radius or hub position of the outermost designated rotors is used. Optionally the wing span can be calculated from an appropriate specification of all wing-panel widths. The wing is at position z F , where the aerodynamic forces act. The component axes are the aircraft body axes, C BF = I. The wing planform is defined in terms of one or more wing panels (fig. 13-1). Symmetry of the wing is assumed. The number of panels is P , with the panel index p =1to P . The span station η is scaled with the semi-span: y = η(b/2), η =0to 1. Each panel is a trapezoid, with a straight aerodynamic center and linear taper. The aerodynamic-center locus (in wing axes) is defined by sweep Λp; dihedral δp; and offsets (xIp, zIp) at the inboard edge relative to the aerodynamic center of the previous panel. The wing position z F is the mean aerodynamic center. The offset (¯xA, ¯zA) of the mean aerodynamic center from the root-chord aerodynamic center is calculated (so the wing planform can be drawn; typically the aerodynamic center is drawn as the quarter-chord). Outboard panel edges are at ηEp (input or calculated). A panel is characterized by span bp (each side), mean chord cp, and area Sp =2bpcp (both sides). The taper is defined by inboard and outboard chord ratios, λ = c/cref (where cref is a panel or wing reference chord, depending on the options for describing the geometry). The span for each panel (if there are more than two panels) can be a fixed input; a fixed ratio of the wing span, bp = fbp(b/2); or free. The panel outboard edge (except at the wing tip) can be at a fixed input position yEp; atafixed station ηEp, yp = ηEp(b/2); calculated from the fuselage and rotor geometry, yp = fR + dfus + 1/2wfus (for a designated rotor); calculated from the hub position, yp = |yhub| (for a designated rotor); or adjusted. An adjusted station is obtained from the last station and the span of this
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NASA/TP-2009-215402 NDARC NASA Desi
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NASA/TP-2009-215402 NDARC NASA Desi
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TABLE OF CONTENTS CHAPTER 1 - INTRO
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TABLE OF CONTENTS (cont.) CHAPTER 1
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viii LIST OF FIGURES (cont.) Figure
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Chapter 1 Introduction The NASA Des
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Introduction 3 of rotorcraft config
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Introduction 5 previous case DESIGN
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Introduction 7 4) Scully, M.; and F
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Chapter 2 Nomenclature The nomencla
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Nomenclature 11 Fuel Tanks Power Na
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Nomenclature 13 Motion aF AC aircra
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Chapter 3 Tasks The NDARC code perf
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Tasks 17 engine group is found (inc
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Tasks 19 3-4 Maps 3-4.1 Engine Perf
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Chapter 4 Operation 4-1 Flight Cond
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Operation 23 e) Input payload weigh
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Operation 25 Table 4-1. Mission seg
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Operation 27 horizontal ground dist
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Operation 29 climb for zero power m
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Operation 31 a) Horizontal velocity
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Operation 33 From the pressure p =
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Chapter 5 Solution Procedures The N
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Solution Procedures 37 Sizing Task
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Solution Procedures 39 relaxation i
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Solution Procedures 41 Table 5-4. T
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Solution Procedures 43 successive s
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Solution Procedures 45 initialize e
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Chapter 6 Cost Costs are estimated
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Cost 49 Table 6-1. DoD and CPI infl
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Cost 51 predicted base price (1994$
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Chapter 7 Aircraft The aircraft con
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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
Page 79 and 80: Aircraft 67 WEIGHT EMPTY STRUCTURE
Page 81 and 82: Chapter 8 Systems The systems compo
Page 83 and 84: Chapter 9 Fuselage There is one fus
Page 85 and 86: Fuselage 73 αe = αfus − αzl, w
Page 87 and 88: Chapter 10 Landing Gear There is on
Page 89 and 90: 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
Page 103 and 104: Rotor 91 TPP tilt / cyclic magnitud
Page 105 and 106: Rotor 93 with an average over the r
Page 107 and 108: Rotor 95 (all equal to 1 for μz =0
Page 109 and 110: Rotor 97 κ 1.30 1.25 1.20 1.15 1.1
Page 111 and 112: Rotor 99 (C T /σ) s c d mean 0.20
Page 113 and 114: Rotor 101 11-5.1.3 Twin Rotors For
Page 115 and 116: Rotor 103 The wake is a skewed cyli
Page 117 and 118: Rotor 105 weight per lifting rotor;
Page 119: Chapter 12 Force The force componen
Page 123 and 124: Wing 111 denotes outboard edge, sub
Page 125 and 126: Wing 113 13-3.1 Lift The wing lift
Page 127 and 128: Wing 115 The wing interference at t
Page 129 and 130: Chapter 14 Empennage The aircraft c
Page 131 and 132: Empennage 119 14-4 Weights The tail
Page 133 and 134: Chapter 15 Fuel Tank 15-1 Fuel Capa
Page 135 and 136: Fuel Tank 123 if Wfuel >Wfuel−max
Page 137 and 138: Chapter 16 Propulsion The propulsio
Page 139 and 140: Propulsion 127 If the sum of the fi
Page 141 and 142: Chapter 17 Engine Group The engine
Page 143 and 144: Engine Group 131 The engine group p
Page 145 and 146: Engine Group 133 specific fuel cons
Page 147 and 148: Chapter 18 Referred Parameter Turbo
Page 149 and 150: Referred Parameter Turboshaft Engin
Page 159 and 160: Chapter 19 AFDD Weight Models This
Page 161 and 162: AFDD Weight Models 149 The spar-cap
Page 163 and 164: AFDD Weight Models 151 19-1.2 Aircr
Page 165 and 166: AFDD Weight Models 153 where w = nz
Page 167 and 168: AFDD Weight Models 155 units as use
Page 169 and 170: 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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