The basic lift vs. weight / thrust vs drag drawing you probably learned in basic flight school was technically wrong: one of those forces doesn't really exist and another isn't really what you think it is.
It was, however, enough to get you off the ground and it probably continues to serve you well today. But if you really want to understand how your airplane seems to defy gravity and how to get every ounce of performance from it, you need to understand what drag really is and it all starts with that diagram.
Everything here is from the references shown below, with a few comments in an alternate color.
Recall from our discussions about lift, that lift itself really doesn't exist. The real forces pulling, tugging, pushing, or in some other way exerting a force on an aircraft are:
In the diagram these forces are shown in red. What of the forces shown in black? They are the two components of aerodynamic force resolved parallel and perpendicular to the relative wind. The force perpendicular to the relative wind is lift and is covered more fully under the lift section. The force parallel to the relative wind is drag. Drag comes in two forms: induced and parasite.
Induced drag is a difficult concept to understand, though its effects are clearly seen in a wind tunnel. Perhaps the best way to introduce the concept is to consider how an airfoil with no ends would behave, as impossible as that may be, and then look at what happens when we introduce a wing tip.
The so-called infinite wing displaces air for a while, but the air particles return to their original positions along the relative wind. The relative wind experience up wash as it approaches the airfoil and down wash as it leaves the airfoil. But the up wash and down wash are equal so the net effect is cancelled. Because of this, the aerodynamic force occurs perpendicular to the relative wind and their is no induced drag. In other words, all of the aerodynamic force is producing lift, none of it is pulling the wing backwards.
A finite wing, that is one with wing tips, cuts through the air with higher pressure on the bottom than the top. Some of this pressure spills over at the tips and curls inboard. Because the wing is moving forward, the air curling inboard and aft hits the trailing edge airstream and pushes it downward.
The vortices push down on the trailing edge airstream which deflects the aerodynamic force aft. It is no longer acting perpendicular to the relative wind. A perpendicular component continues to lift the airfoil while a parallel component exerts a force aft. This force is Draginduced.
Parasite drag is what most people think about when considering drag:
When plotted against speed, parasite drag starts at zero and goes up. Induced drag starts when the wing start producing lift at high angles of attack and is very high, but then decreases as speed increases. The two speeds added together make up total drag and where total drag is at a minimum, Draginduced = Dragparasite and each is equal to one-half of total drag.
Basic Lift Equation: L = CL q S
The coefficient of lift, as shown on the graph, starts small and increases with increasing angle of attack. There comes a point, however, where lift reaches a maximum and drops off.
The coefficient of drag, on the other hand, starts small and increases with increasing angle of attack with no end.
The drag equation is similar to the equation for lift:
14 CFR 25, Title 14: Aeronautics and Space, Federal Aviation Administration, Department of Transportation
Air Training Command Manual 51-3, Aerodynamics for Pilots, 15 November 1963
Connolly, Thomas F., Dommasch, Daniel 0., and Sheryby, Sydney S., Airplane Aerodynamics, Pitman Publishing Corporation, New York, NY, 1951.
Davies, D. P., Handling the Big Jets, Civil Aviation Authority, Kingsway, London, 1985.
Dole, Charles E., Flight Theory and Aerodynamics, 1981, John Wiley & Sons, Inc, New York, NY, 1981.
FAA-H-8083-15, Instrument Flying Handbook, U.S. Department of Transportation, Flight Standards Service, 2001.
Gulfstream G450 Airplane Flight Manual, Revision 35, April 18, 2013.
Gulfstream G450 Aircraft Operating Manual, Revision 35, April 30, 2013.
Hage, Robert E. and Perkins, Courtland D., Airplane Peformance Stability and Control, John Wiley & Sons, Inc., 1949.
Hurt, H. H., Jr., Aerodynamics for Naval Aviators, Skyhorse Publishing, Inc., New York NY, 2012.
Technical Order 1T-38A-1, T-38A/B Flight Manual, USAF Series, 1 July 1978.
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