book a.c. stability

Sheet1Longitudinal StabilityFuselage LengthL (f)126Wing Center of LiftL_ctr (x/L)0.6m.a.c. (ft)27.2Load Summary (fuselage)Load TypeMagnitudex/L_startx/L_endresultantM @C_liftdw(lbs)x/Lf-lb (+ cw)Fuel412610.40.60.5-519888.68252.2Payload40000.10.80.45-75600266.6666666667Fus.Struct.9977010.5-125710.2475.0952380952Engine(s)130000.70.70.716380013000Wing Struct.41220.40.80.60.0000000001458Horiz. Tail2280.150.20.175-12209.4114Vert. Tail3340.810.912625.266.8Other16202010.5-204145.2771.5238095238S L89124S M-761128.2Tail Lift (req)14213.41176470590.150.20.175-761128.27106.7058823529Center of GravityX_cg / L0.5322213994X_cg (ft)67.0598963242fStatic MarginS.M.0.3139743998stableLongitudinal Stability Coefficient:Wing Parameters:S_w831f^2(C_L_a)_w0.044(deg)^-1x_w-8.5401036758fcbar27.2fHoriz. Tail Paramters:(C_L_a)_ht0.03(deg)^-1de/da0Fig. 11.3h_ht1l_ht-45.0098963242fS_ht74f^2Engine Parametersmdot135.4lbm/sl_i1.6frho0.0092lbm/f^3V1925.7f/sdb/da1CalculationsV_bar_hs-0.147356672inlet effect0.0000099543unstablewing effect-0.7915339514stablecheck: C_M_a =-S.M.*C_L_a-0.7915339514h. tail effect-0.2532874616stableC_M_a-0.5382564441stableDirectional Stability Coefficient:Wing Parameters:A_w2L62degl0S_w831f^2b40.8fz_w-4fC_L (cruise)0.201Fuselage Parameters:h9fw9fVol_f3990f^3Vertical Tail Parameters:(C_L_a)_vs0.023(deg)^-1l_vs46.3401036758fS_vs100f^2L_vs63degCalculationsV_bar_vs0.1366771185(1+ds/db)q/q0.8174776919Eq[11.42]v. tail effect0.147238774Eq[11.40]stablefuse. effect-0.1529871877Eq[11.44]unstablewing effect0.0091767532Eq[11.43]stableC_n_b0.0034283396stableC_L_b-0.0034283396stableRudder SizingInput Parametersd_r20degb11.5degAsym. T10200lbsS_w831f^2b40.8fC_n_b0.0034283396diam_e2.79fV_T-O303f/srho_T-O0.068lbm/f^3Calculations1.2V_T-O363.6f/s0.2V_T-O60.6f/sq139.5952993789lbs/f^2D_e1024.1187758156lbsC_n_dR:Asy. Power0.0067938024[rad]^-1Eq[11.47]Cross Wind-0.0019712953[rad]^-1Eq[11.50]da_0L/dd_r0.0419106231Eq[11.51]C_R/C_VS4%Fig. 11.9

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