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Excellent question! Yes indeed, it does! At least in the sense that it is pushing the carrier down. Now we have an intense discussion going on if this is weight or not. If we avoid the nitpickers and …

We don't need to look at the infinite case to see where the error in your thought experiment is. It will be sufficient to see what is different between a hovering rotor and an ascending one. Basically …

Note that the inertias are defined in the body axis system. Not all the main inertial axes are aligned with the body axis system: The high nose section and the low engines combine to tilt the inertial …

Maybe I should have a word with Martin Hepperle, but the way he displays the force is how you will find it in the literature, too. Please note that in addition to the lift vector at the neutral point, …

Yes, it does make sense. However, the angle of attack increase of the tailwheel airplane would only be possible if it touches down on the main wheels while there still is much clearance of the tail wh …

Normally this is in the tens of seconds. An approximation for the undamped phygoid frequency is: $$\omega_P = \frac{2\cdot g}{v}\cdot \left(1-\frac{c_{mv}\cdot c_{L\alpha}}{c_L\cdot c_{m\alpha}}\righ …

Not much if designed for it, but efficiency will suffer. Also, if the blade is not designed for the loads, the all-supersonic flow could overload it. How would you achieve the desired all-supersonic …

Let the initial state have the index 1. If drag is $D$, then $P_1$ is: $$P_1 = D_1\cdot v\;\; \text{or} \;\;\frac{\rho}{2}\cdot v^3\cdot S_{ref}\cdot\left(c_{D0}+\frac{c_L^2}{\pi\cdot AR\cdot\epsilon} …

Let's look at the extreme case of a 90° pitch attitude. The airplane climbs vertically. Thankfully, in case of an F-16 without loads this is possible (left side of sketch below). The vertical load fa …

This is not a dumb question at all, and the short answer is not at all. Since the fuselage must be balanced around the center of gravity (cg), part of it will be forward of the cg. This part contribut …

The polar point for maximum flight time only coincides with the minimum drag point when engine thrust does not change over speed. This is approximately true for pure turbojets and rockets. If thrust c …

Your question shows that you know that the speed of sound is the speed of small pressure changes in a fluid, and moving faster than that will give the fluid ahead no warning of an approaching disturba …

The term $$V_q\cdot{sin}\theta_t$$ is a speed, not a force, so it cannot be an accurate expression of the thrust vector. Propellers accelerate the air flowing through the propeller disc in the direc …

Not thermal contraction but condensation of vapor is a problem. Immediately, fuselage pressurization is the far bigger problem that comes with the altitude changes. But if you operate in hot and mois …

The airfoil affects the lift curve slope only very little; theoretically the slope should be a bit steeper for thicker airfoils. But that pales in comparison to the effects of wing planform. Here the …