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48 Cost and using additional factors 0.8754 (pressurized) or 0.7646 (unpressurized). The other terms in the operating cost are: Cfuel = G(Wfuel/ρfuel)Ndep Ccrew =3.19 KcrewW 0.4 MTOB Cins =0.0056 CAC 1+S Cdep = CAC (1 − V ) D 1+S 2L +1 i Cfin = CAC D 4 100 The fuel burn Wfuel, block time Tmiss, and block range Rmiss are obtained for a designated mission. The number of departures per year is Ndep = B/Tmiss. The flight time per trip is Ttrip = Tmiss − TNF. The flight hours per year are TF = TtripNdep. The yearly operating cost COP and DOC+Iare then: COP = TF Cmaint + Cfuel + Ccrew + Cdep + Cins + Cfin DOC + I = 100 COP /ASM where the available seat miles per year are ASM = 1.1508NpassRmissNdep. Parameters are defined in table 6-2, including units as used in these equations.
Cost 49 Table 6-1. DoD and CPI inflation factors. inflation factors inflation factors inflation factors year DoD CPI year DoD CPI year DoD CPI 1911 1951 17.02 17.54 1991 93.99 91.90 1912 1952 16.26 17.88 1992 96.21 94.67 1913 6.68 1953 16.31 18.02 1993 98.16 97.50 1914 6.75 1954 16.02 18.15 1994 100.00 100.00 1915 6.82 1955 17.29 18.08 1995 101.73 102.83 1916 7.35 1956 17.58 18.35 1996 103.25 105.87 1917 8.64 1957 18.17 18.96 1997 104.41 108.30 1918 10.19 1958 18.02 19.50 1998 105.47 109.99 1919 11.67 1959 18.11 19.64 1999 106.88 112.42 1920 13.50 1960 18.34 19.97 2000 108.46 116.19 1921 12.08 1961 18.31 20.18 2001 109.99 119.50 1922 11.34 1962 18.84 20.38 2002 111.63 121.39 1923 11.54 1963 19.09 20.65 2003 113.88 124.16 1924 11.54 1964 19.76 20.92 2004 116.81 127.46 1925 11.81 1965 20.36 21.26 2005 120.04 131.78 1926 11.94 1966 21.97 21.86 2006 123.05 136.03 1927 11.74 1967 22.77 22.54 2007 125.67 139.91 1928 11.54 1968 24.03 23.48 2008 127.67 145.28 1929 11.54 1969 25.10 24.76 2009* 129.37 1930 11.27 1970 25.76 26.18 2010* 131.22 1931 10.26 1971 27.24 27.33 2011* 133.41 1932 9.24 1972 28.98 28.21 2012* 135.77 1933 8.77 1973 31.34 29.96 2013* 138.26 1934 9.04 1974 34.13 33.27 2014* 140.72 1935 9.24 1975 38.10 36.30 2015* 143.25 1936 9.38 1976 42.14 38.39 1937 9.72 1977 43.75 40.89 1938 9.51 1978 47.82 43.99 1939 9.38 1979 53.02 48.99 1940 9.45 1980 58.52 55.60 1941 9.92 1981 63.80 61.34 1942 11.00 1982 68.35 65.11 1943 11.67 1983 71.92 67.21 1944 11.88 1984 74.57 70.11 1945 12.15 1985 76.86 72.60 1946 13.16 1986 79.19 73.95 1947 15.05 1987 81.87 76.65 1948 16.26 1988 85.01 79.82 1949 16.06 1989 88.19 83.67 1950 15.37 16.26 1990 91.30 88.19 * projected
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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
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 and 24: Nomenclature 11 Fuel Tanks Power Na
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: Chapter 6 Cost Costs are estimated
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
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
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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
Page 125 and 126:
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 157 and 158:
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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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