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of advanced aircraft concepts. Two input files for all modules are discussed. Representative examples of benefit analyses are shown. User's Manual D.9 Executive System Misc. Data Normal moduli () .437E+7 pai Shear moduli (3) Gf3 .38E48 Thermal expansion coef. Alfa m .4E- in/in/F Matrix heat conductivity Km .SE-«-S Matrix conpresslve strth SmC .E- in/in Allowable con^r. strain eps nC .3B+ in/in Allowable torsional strain eps mS .3E- in/in Allowable torsional strain eps niT .8E- In/in Allowable torsional strain eps mS . 3E-I- in/in Allowable coiapr. strain eps niT .8E- In/in Allowable shear strain eps mC .E4 in/in Allowable cotupx. strain eps tRXOR .4E- in/in Void heat conductivity kv BT-in/hr/in**/F Glass transition ten^erature Tgdr FECR SDPERALLOY (FE-%CR-4%AL-%Y) MATRIX .3E+8 Poisson”s ratio (3) Nu£3 .E-I- non -dim Shear moduli () Ef O.lOSE-i-8 pai Polsson"a ratio () Nu£ .E+ non-dim Poiason"s ratio (3) Nuf3 .38E48 Shear moduli (3) Gf3 .3E+6 Thermal expansion coef. () Alfaf .7E- in/in/F Matrix heat conductivity Jcv BT-in/hr/in**/F Glass transition ten^rature Tgdr TI TITANIDM MATRIX. ADG , .7E+ lb/in**3 Normal moduli () Efll ..4E-I-8 Poisson"s ratio () Nu£ .3E+ non-dim Shear moduli (3) Gf3 .E-I-8 pai Shear moduli () Gfl
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