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Performance (Rate of Climb - Ch 7 PRat Power = RoC Why The French…

- - - - The max SnL CAS is achieved at low level
        
        The max SnL TAS is achieved at high altitude
        
        CAS will always decrease with alt. TAS will increase …till the CAS rate of reduction is greater
- - - - MMR (Max Range Mach) = 1.32Vmd = tangent to the drag curve (best ratio of TAS to Drag)
      - Optimum Altitude where T from engines @ optimum 90% RPM bring T line to 1.32Vmd = MMR
        
        Greatest TAS for same CAS (and thus drag)
        
        As fuel ⬇, mass ⬇, curve moves down and left so tangent will be lower which means ALTITUDE ⬆ in order to reach 1.32Vmd again
      - Stepped climb to maintain optimum alt.
    - - Optimum Altitude for PISTON prop = Full Throttle Height set my manufacturer
        
        Optimum Altitude for TURBOPROP = Medium to High set my manufacturer
        
        * Altitude less important , only determined by engine and propellor efficiency
      - Max Range Speed = 1.32Vmp = tangent to the power curve (best ratio of TAS to Power Required)
    - - Wind :
        
        SAR is unaffected by wind
        
        SGR is wind affected:
        ** headwind reduces SGR (shift start of tangent right)
        ** tailwind increases SGR (shift start of tangent left)
        
        The effect of wind on SGR can be summarised by the adage "get out of a headwind (fly faster) and stay in a tailwind (fly slower)"
      - Mass increase:
        
        decreases the SR
        
        increases the best range speed (1.32Vmd and Mmr)
      - Altitude :
        
        Range is max only at the optimum altitude
        
        Above or below that SR decreases
    - - ECON (economy) profile is then available , which determines the cruise Mach number (Mecon) based on the cost index
        
        As the cost index increases Mecon increases