I was wondering if anyone could explain this to me. If an airplane is in a 1-g state and then is manuvered to a 0 g state, what happens to induced and parasite drag?
Depends on how you reach this "0-G state".
If you fly an 'over-the-top' arc, such as, you are at cruise speed and pull back to climb and pull the speed back to Va, then push over to attain 0-G while keeping Va, the lift/drag will be the same at that speed, whether you are level or turning or attaining more or less than 1 G.
If you attain this '0-G state' by pulling straight up until you zero out the airspeed and literally fall back, during this moment of reversal of direction, you will be at 0 G, but also at zero airspeed, so there will also be no drag.
Induced drag is caused by lift. As long as the wing is creating lift (which it is at 0g), there is induced drag.
Edit: Parasite drag is drag caused by all the little bumps, rivets, antenna, etc. At 0g, as long as air is still flowing over the body of the aircraft, the parasite drag isn't changing much at all.
Induced drag is a function of angle of attack, and varies with AoA and the lift the airfoil is producing. Induced drag is produced when lift is produced, but isn't a function of lift; it's a function of AoA. At a minimal AoA or a negative AoA, the value of induced drag is considerably lessened, though not completely eliminated.
Likewise, parastic drag is also affected by the surface exposed to the slipstream, and in an unloaded or zero G condition, while no specific change in EAS or TAS may occur, the exposed wetted or flat plate area, as well as what is actually exposed to the slipstream, may change substantially, resulting in chages in parasitic drag
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