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Earll Murman is an aerospace engineer and MIT professor emeritus whose institutional profile identifies aircraft systems engineering among his specializations. His authored lecture on aircraft performance connects aerodynamic forces, propulsion, energy and maneuvering constraints. The lecture title page credits him directly and is dated 18 September 2003; the host course is a separate Fall 2004 offering.^[ref][ref]

One useful connection in that lecture is aircraft energy height. For constant mass $m$, gravitational acceleration $g$, altitude $h$ and true airspeed $V$ in a still-air model, divide the sum of gravitational potential energy and kinetic energy by gravitational weight:If thrust $T$ acts along the motion, drag $D$ opposes it, and other energy exchanges are neglected, the specific excess power isThis expresses the possibility of using the available mechanical power for climbing, accelerating, or both.^[ref]

For an original stipulated example, take $m=1000\mathrm{kg}$, $g=9.81m/{\mathrm{s}}^2$, $V=50m/s$ and $T-D=300\mathrm{N}$. Then $P_s\simeq 1.529m/s$. At constant true airspeed, that is the model's climb rate. At constant altitude, the same instantaneous power gives $dV/dt=0.30m/{\mathrm{s}}^2$. These are alternative allocations at the stipulated condition, not a claim that an actual engine maintains the same excess thrust throughout a maneuver.

The distinction illustrates why satisfying a lift or aerodynamic load factor requirement alone does not establish sustained performance. Measurements of speed change, altitude change, thrust and drag test different terms of the energy account. The lecture's force and energy models make those assumptions explicit; they do not replace configuration-specific experimental data.