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40 Solution Procedures
Table 5-1. Maximum-effort solution.
maximum effort variable initial increment tolerance
horizontal velocity Vh 0.1V Δ 0.1Vɛ
vertical rate of climb Vz 0.1V Δ 0.1Vɛ
aircraft altitude HΔ Hɛ
aircraft angular rate ˙ θ (pullup), ˙ ψ (turn) ΩΔ Ωɛ
aircraft linear acceleration ax, ay, az GΔ Gɛ
Table 5-2. Maximum-effort solution.
maximum effort quantity
best endurance maximum 1/ ˙w
best range 99% maximum V/ ˙w high or low side, or 100%
best climb or descent rate maximum Vz or 1/P
best climb or descent angle maximum Vz/V or V/P
ceiling maximum altitude
power limit power margin, min(PavP G − PreqPG) =0 over all propulsion groups
torque limit torque margin, min(Qlimit − Qreq) =0 over all limits
wing stall lift margin, CLmax − CL =0 for designated wing
rotor stall thrust margin, (CT /σ)max − CT /σ =0 for designated rotor
Table 5-3. Trim solution.
trim quantity target tolerance
aircraft total force x, y, z components 0 Fɛ
aircraft total moment x, y, z components 0 Mɛ
aircraft load factor x, y, z components Flight State ɛ
propulsion group power Flight State Pɛ
power margin PavP G − PreqPG Flight State Pɛ
rotor force lift, vertical, propulsive Flight State, component schedule Fɛ
rotor thrust CT /σ Flight State Cɛ
rotor thrust margin (CT /σ)max − CT /σ Flight State Cɛ
rotor flapping βc, βs Flight State Aɛ
rotor hub moment x (roll), y (pitch) Flight State Mɛ
rotor torque Flight State Mɛ
wing force lift Flight State, component schedule Fɛ
wing lift coefficient CL Flight State Cɛ
wing lift margin CLmax − CL Flight State Cɛ
tail force lift Flight State Fɛ