Bernoilli_equation

Bernoulli\'s equation redirects here; see Bernoulli differential equation for an unrelated topic in ordinary differential equations.

In fluid dynamics, Bernoulli\'s principle states that for a fluid, an increase in the speed of the fluid occurs simultaneously with a decrease in pressure or a decrease in the fluid\'s gravitational potential energy.Clancy, L.J., (1975), Aerodynamics, Chapter 3, Pitman Publishing Limited, London Bernoulli\'s principle is named in honor of Daniel Bernoulli.

The simple form of Bernoulli\'s principle is valid for incompressible flows (e.g. most liquid flows) and also for compressible flows (e.g. gases) moving at low Mach numbers. More advanced forms may in some cases be applied to compressible flows at high Mach numbers (see the derivations of the Bernoulli equation).

Bernoulli\'s principle is equivalent to the principle of conservation of energy. This states that the sum of all forms of mechanical energy in a fluid along a streamline is the same at all points on that streamline. This requires that the sum of kinetic energy and potential energy remains constant. If the fluid is flowing out of a reservoir the sum of all forms of energy is the same on all streamlines because in a reservoir the energy per unit mass (the sum of pressure and gravitational potential $\backslash rho\; g\; h$) is the same everywhere. Streeter, V.L., Fluid Mechanics, Example 3.5, McGraw-Hill Inc. (1966), New York

Fluid particles are subject only to pressure and their own weight. If a fluid is flowing horizontally and along a section of a streamline, where the speed increases it can only be because the fluid on that section has moved from a region of higher pressure to a region of lower pressure; and if its speed decreases, it can only be because it has moved from a region of lower pressure to a region of higher pressure. Consequently, within a fluid flowing horizontally, the highest speed occurs where the pressure is lowest, and the lowest speed occurs where the pressure is highest.

Contents 1 Incompressible flow equation 1.1 Simplified form 1.2 Applicability of incompressible flow equation to flow of gases 2 Compressible flow equation 2.1 Compressible flow in fluid dynamics 2.2 Compressible flow in thermodynamics 3 Derivations of Bernoulli equation 4 Real World Application 5 A common misconception about wings 5.1 Stick and Rudder 5.2 Understanding Flight 5.3 Equal transit-time fallacy 6 References 7 See also 8 External links

Incompressible flow equation

In most flows of liquids, and of gases at low Mach number, the mass density of a fluid parcel can be considered to be constant, regardless of pressure variations in the flow. For this reason the fluid in such flows can be considered to be incompressible and these flows can be described as incompressible flow. Bernoulli performed his experiments on liquids and his equation in its original form is valid only for incompressible flow.

The original form of Bernoulli\'s equationClancy, L.J., Aerodynamics, Section 3.4 is:

$\{v^2\; \backslash over\; 2\}+gh+\{p\backslash over\backslash rho\}=\backslash mathrm\{constant\}$

where:

$v\backslash ,$ is the fluid velocity at a point on a streamline

$g\backslash ,$ is the acceleration due to gravity

$h\backslash ,$ is the height of the point above a reference plane

$p\backslash ,$ is the pressure at the point

$\backslash rho\backslash ,$ is the density of the fluid at all points in the fluid

The following assumptions must be met for the equation to apply:

• The fluid must be incompressible - even though pressure varies, the density must remain constant.
• The streamline must not enter the boundary layer. (Bernoulli\'s equation is not applicable where there are viscous forces, such as in the boundary layer.)

The above equation can be rewritten as:

$\{\backslash rho\; v^2\; \backslash over\; 2\}+\backslash rho\; gh+p=q+\backslash rho\; gh+p=\backslash mathrm\{constant\}$

where:

$q\; =\; \backslash frac\{\backslash rho\; v^2\}\{2\}$ is dynamic pressure

The above equations suggest there is a velocity at which pressure is zero and at higher velocities the pressure is negative. Gases and liquids are not capable of negative absolute pressure, or even zero pressure, so clearly Bernoulli\'s equation ceases to be valid before zero pressure is reached. The above equations use a linear relationship between velocity squared and pressure. At higher velocities in liquids, non-linear processes such as (viscous) turbulent flow and cavitation occur. At higher velocities in gases the changes in pressure become significant so that the assumption of constant density is invalid.

Simplified form

In many applications of Bernoulli\'s equation, the change in the $\backslash rho\backslash ,gh$ term along streamlines is zero or so small it can be ignored. This allows the above equation to be presented in the following simplified form:

$p\; +\; q\; =\; p\_0\backslash ,$

where $p\_0\backslash ,$ is called total pressure, and $q\backslash ,$ is dynamic pressureNASA\'s guide to Bernoulli\'s Equation. Many authors refer to the pressure $p\backslash ,$ as static pressure to distinguish it from total pressure $p\_0\backslash ,$ and dynamic pressure $q\backslash ,$. In Aerodynamics, L.J. Clancy writes: "To distinguish it from the total and dynamic pressures, the actual pressure of the fluid, which is associated not with its motion but with its state, is often referred to as the static pressure, but where the term pressure alone is used it refers to this static pressure."Clancy, L.J., Aerodynamics, Section 3.5

The simplified form of Bernoulli\'s equation can be summarized in the following memorable word equation:

static pressure + dynamic pressure = total pressureClancy, L.J., Aerodynamics, Section 3.5

Every point in a steadily flowing fluid, regardless of the fluid speed at that point, has its own unique static pressure $p$, dynamic pressure $q$, and total pressure $p\_0$.

The significance of Bernoulli\'s principle can now be summarized as "total pressure is constant along a streamline." Furthermore, if the fluid flow originated in a reservoir, the total pressure on every streamline is the same and Bernoulli\'s principle can be summarized as "total pressure is constant everywhere in the fluid flow." However, it is important to remember that Bernoulli\'s principle does not apply in the boundary layer.

Applicability of incompressible flow equation to flow of gases

Bernoulli\'s equation is sometimes valid for the flow of gases provided that there is no transfer of kinetic or potential energy from the gas flow to the compression or expansion of the gas. If both the gas pressure and volume change simultaneously, then work will be done on or by the gas. In this case, Bernoulli\'s equation can not be assumed to be valid. However if the gas process is entirely isobaric, or isochoric, then no work is done on or by the gas, (so the simple energy balance is not upset). According to the gas law, an isobaric or isochoric process is ordinarily the only way to ensure constant density in a gas. Also the gas density will be proportional to the ratio of pressure and absolute temperature, however this ratio will vary upon compression or expansion, no matter what non-zero quantity of heat is added or removed. The only exception is if the net heat transfer is zero, as in a complete thermodynamic cycle, or in an individual isentropic (frictionless adiabatic) process, and even then this reversible process must be reversed, to restore the gas to the original pressure and specific volume, and thus density. Only then is the original, unmodified Bernoulli equation applicable. In this case the equation can be used if the velocity of the gas is sufficiently below the speed of sound, such that the variation in density of the gas (due to this effect) along each streamline can be ignored. Adiabatic flow at less than Mach 0.3 is generally considered to be slow enough.

Compressible flow equation

Bernoulli developed his principle from his observations on liquids, and his equation is applicable only to incompressible fluids, and compressible fluids at very low speeds (perhaps up to 1/3 of the sound velocity in the fluid). It is possible to use the fundamental principles of physics to develop similar equations applicable to compressible fluids. There are numerous equations, each tailored for a particular application, but all are analogous to Bernoulli\'s equation and all rely on nothing more than the fundamental principles of physics such as Newton\'s laws of motion or the first law of thermodynamics.

Compressible flow in fluid dynamics

A useful form of the equation, suitable for use in compressible fluid dynamics, is:

$\backslash left(\backslash frac\; \{\backslash gamma\}\{\backslash gamma-1\}\backslash right)\backslash frac\; \{p\}\{\backslash rho\}\; +\; \backslash frac\; \{v^2\}\{2\}\; +\; gh\; =\; \backslash mathrm\{constant\}$Clancy, L.J., Aerodynamics, Section 3.11 (constant along a streamline)

where:

$\backslash gamma\backslash ,$ is the ratio of the specific heats of the fluid

$p\backslash ,$ is the pressure at a point

$\backslash rho\backslash ,$ is the density at the point

$v\backslash ,$ is the speed of the fluid at the point

$g\backslash ,$ is the acceleration due to gravity

$h\backslash ,$ is the height of the point above a reference plane

In many applications of compressible flow, changes in height above a reference plane are negligible so the term $gh\backslash ,$ can be omitted. A very useful form of the equation is then:

$\backslash left(\backslash frac\; \{\backslash gamma\}\{\backslash gamma-1\}\backslash right)\backslash frac\; \{p\}\{\backslash rho\}\; +\; \backslash frac\; \{v^2\}\{2\}\; =\; \backslash left(\backslash frac\; \{\backslash gamma\}\{\backslash gamma-1\}\backslash right)\backslash frac\; \{p\_0\}\{\backslash rho\_0\}$

where:

$p\_0\backslash ,$ is the total pressure

$\backslash rho\_0\backslash ,$ is the total density

Compressible flow in thermodynamics

Another useful form of the equation, suitable for use in thermodynamics, is:

$\{v^2\; \backslash over\; 2\}+\; gh\; +\; w\; =\backslash mathrm\{constant\}$Van Wylen, G.J., and Sonntag, R.E., (1965), Fundamentals of Classical Thermodynamics, Section 5.9, John Wiley and Sons Inc., New York

$w\backslash ,$ is the enthalpy per unit mass, which is also often written as $h\backslash ,$ (which would conflict with the use of $h\backslash ,$ for "height" in this article).

Note that $w\; =\; \backslash epsilon\; +\; \backslash frac\{p\}\{\backslash rho\}$ where $\backslash epsilon\; \backslash ,$ is the thermodynamic energy per unit mass, also known as the specific internal energy or "sie."

The constant on the right hand side is often called the Bernoulli constant and denoted $b\backslash ,$. For steady inviscid adiabatic flow with no additional sources or sinks of energy, $b\backslash ,$ is constant along any given streamline. More generally, when $b\backslash ,$ may vary along streamlines, it still proves a useful parameter, related to the "head" of the fluid (see below).

When the change in $gh\backslash ,$ can be ignored, a very useful form of this equation is:

$\{v^2\; \backslash over\; 2\}+\; w\; =\; w\_0$

where $w\_0\backslash ,$ is total enthalpy.

When shock waves are present, in a reference frame moving with a shock, many of the parameters in the Bernoulli equation suffer abrupt changes in passing through the shock. The Bernoulli parameter itself, however, remains unaffected. An exception to this rule is radiative shocks, which violate the assumptions leading to the Bernoulli equation, namely the lack of additional sinks or sources of energy.

Derivations of Bernoulli equation

Bernoulli equation for incompressible fluids

The Bernoulli equation for incompressible fluids can be derived by integrating the Euler equations, or applying the law of conservation of energy in two sections along a streamline, ignoring viscosity, compressibility, and thermal effects. The simplest derivation is to first ignore gravity and consider constrictions and expansions in pipes that are otherwise straight, as seen in Venturi effect. Let the x axis be directed down the axis of the pipe. The equation of motion for a parcel of fluid on the axis of the pipe is $m\; \backslash frac\{dv\}\{dt\}=\; -F$ $\backslash rho\; A\; dx\; \backslash frac\{dv\}\{dt\}=\; -A\; dp$ $\backslash rho\; \backslash frac\{dv\}\{dt\}=\; -\backslash frac\{dp\}\{dx\}$ In steady flow, $v=v(x)$ so $\backslash frac\{dv\}\{dt\}=\; \backslash frac\{dv\}\{dx\}\backslash frac\{dx\}\{dt\}\; =\; \backslash frac\{dv\}\{dx\}v=\backslash frac\{d\}\{dx\}\; \backslash frac\{v^2\}\{2\}$ With $\backslash rho$ constant, the equation of motion can be written as $\backslash frac\{d\}\{dx\}\; \backslash left(\; \backslash rho\; \backslash frac\{v^2\}\{2\}\; +\; p\; \backslash right)\; =0$ or $\backslash frac\{v^2\}\{2\}\; +\; \backslash frac\{p\}\{\backslash rho\}=\; C$ where $C$ is a constant, sometimes referred to as the Bernoulli constant. It is not a universal constant, but rather a constant of a particular fluid system. We deduce that where the speed is large, pressure is low and vice versa. In the above derivation, no external work-energy principle is invoked. Rather, the work-energy principle was inherently derived by a simple manipulation of the momentum equation. A streamtube of fluid moving to the right. Indicated are pressure, height, velocity, distance (s), and cross-sectional area. Applying conservation of energy in form of the work-kinetic energy theorem we find that: the change in KE of the system equals the net work done on the system; $W=\backslash Delta\; KE.\; \backslash ;$ Therefore, the work done by the forces in the fluid + decrease in potential energy = increase in kinetic energy. The work done by the forces is $F\_\{1\}\; s\_\{1\}-F\_\{2\}\; s\_\{2\}=p\_\{1\}\; A\_\{1\}\; v\_$ {1}\Delta t-p_{2} A_{2} v_{2}\Delta t. \; The decrease of potential energy is $m\; g\; h\_\{1\}-m\; g\; h\_\{2\}=\backslash rho\; g\; A$ _{1} v_{1}\Delta t h_{1}-\rho g A_{2} v_{2} \Delta t h_{2} \; The increase in kinetic energy is $\backslash frac\{1\}\{2\}\; m\; v\_\{2\}^\{2\}-\backslash frac\{1\}\{2\}\; m\; v\_\{1\}^\{2\}=\backslash frac\{1\}\{2\}\backslash rho\; A\_\{2\}\; v\_\{2\}\backslash Delta\; t\; v\_\{2\}$ ^{2}-\frac{1}{2}\rho A_{1} v_{1}\Delta t v_{1}^{2}. Putting these together, $p\_\{1\}\; A\_\{1\}\; v\_\{1\}\backslash Delta\; t-p\_\{2\}\; A\_\{2\}\; v\_\{2\}\backslash Delta\; t+\backslash rho\; g\; A\_\{1\}\; v\_\{1\}\backslash Delta\; t\; h\_\{1\}-\backslash rho\; g\; A\_\{2\}\; v\_\{2\}\backslash Delta\; t\; h\_\{2\}=\backslash frac\{1\}\{2\}\backslash rho\; A\_\{2\}\; v\_\{2\}\backslash Delta\; t\; v\_\{2\}^\{2\}-\backslash frac\{1\}\{2\}\backslash rho\; A\_\{1\}\; v\_\{1\}\backslash Delta\; t\; v\_\{1\}^\{2\}$ or $\backslash frac\{\backslash rho\; A\_\{1\}\; v\_\{1\}\backslash Delta\; t\; v\_\{1\}^\{$ 2}}{2}+\rho g A_{1} v_{1}\Delta t h_{1}+p_{1} A_{1 } v_{1}\Delta t=\frac{\rho A_{2} v_{2}\Delta t v_{ 2}^{2}}{2}+\rho g A_{2} v_{2}\Delta t h_{2}+p_{2} A_{2} v_{2}\Delta t. After dividing by $\backslash Delta\; t$, $\backslash rho$ and $A\_\{1\}\; v\_\{1\}$ (= rate of fluid flow = $A\_\{2\}\; v\_\{2\}$ as the fluid is incompressible): $\backslash frac\{v\_\{1\}^\{2\}\}\{2\}+g\; h\_\{1\}+\backslash frac\{p\_\{1\}\}\{\backslash rho\}=\backslash frac\{v\_\{2\}^\{2\}\}\{2\}+g\; h\_\{2\}+\backslash frac\{p\_\{2\}\}\{\backslash rho\}$ or, as stated in the first paragraph: $\backslash frac\{v^\{2\}\}\{2\}+g\; h+\backslash frac\{p\}\{\backslash rho\}=C$ (Eqn. 1) Further division by $g\backslash ,$ produces the following equation. Note that each term can be described in the length dimension (such as meters). This is the head equation derived from Bernoulli\'s principle: $\backslash frac\{v^\{2\}\}\{2\; g\}+h+\backslash frac\{p\}\{\backslash rho\; g\}=C$ (Eqn. 2a) The middle term, $h\backslash ,$, can be called head, although height is used throughout this discussion. $h\_\backslash text\{elevation\}\backslash ,$ represents the internal energy of the fluid due to its height above a reference plane. A free falling mass from a height $h\backslash ,$ (in a vacuum) will reach a velocity $v=\backslash sqrt\{\{2\; g\}\{h\}\},$ or when we rearrange it as a head: $h\_\{v\}=\backslash frac\{v^\{2\}\}\{2\; g\}$ The term $\backslash frac\{v^2\}\{2\; g\}$ is called the velocity head, expressed as a length measurement. It represents the internal energy of the fluid due to its motion. The hydrostatic pressure p is defined as $p=\backslash rho\; g\; h\; \backslash ,$, or when we rearrange it as a head: $\backslash psi=\backslash frac\{p\}\{\backslash rho\; g\}$ The term $\backslash frac\{p\}\{\backslash rho\; g\}$ is also called the pressure head, expressed as a length measurement. It represents the internal energy of the fluid due to the pressure exerted on the container. When we combine the head due to the velocity and the head due to static pressure with the elevation above a reference plane, we obtain a simple relationship useful for incompressible fluids. $h\_\{v\}\; +\; h\_\backslash text\{elevation\}\; +\; \backslash psi\; =\; C\backslash ,$ (Eqn. 2b) If we were to multiply Eqn. 1 by the density of the fluid, we would get an equation with three pressure terms: $\backslash frac\{\backslash rho\; v^\{2\}\}\{2\}+\; \backslash rho\; g\; h\; +\; p=C$ (Eqn. 3) We note that the pressure of the system is constant in this form of the Bernoulli Equation. If the static pressure of the system (the far right term) increases, and if the pressure due to elevation (the middle term) is constant, then we know that the dynamic pressure (the left term) must have decreased. In other words, if the speed of a fluid decreases and it is not due to an elevation difference, we know it must be due to an increase in the static pressure that is resisting the flow. All three equations are merely simplified versions of an energy balance on a system.

Bernoulli equation for compressible fluids

The derivation for compressible fluids is similar. Again, the derivation depends upon (1) conservation of mass, and (2) conservation of energy. Conservation of mass implies that in the above figure, in the interval of time $\backslash Delta\; t\backslash ,$, the amount of mass passing through the boundary defined by the area $A\_1\backslash ,$ is equal to the amount of mass passing outwards through the boundary defined by the area $A\_2\backslash ,$: $0=\; \backslash Delta\; M\_1\; -\; \backslash Delta\; M\_2\; =\; \backslash rho\_1\; A\_1\; v\_1\; \backslash ,\; \backslash Delta\; t\; -\; \backslash rho\_2\; A\_2\; v\_2\; \backslash ,\; \backslash Delta\; t$. Conservation of energy is applied in a similar manner: It is assumed that the change in energy of the volume of the streamtube bounded by $A\_1\backslash ,$ and $A\_2\backslash ,$ is due entirely to energy entering or leaving through one or the other of these two boundaries. Clearly, in a more complicated situation such as a fluid flow coupled with radiation, such conditions are not met. Nevertheless, assuming this to be the case and assuming the flow is steady so that the net change in the energy is zero, $0=\; \backslash Delta\; E\_1\; -\; \backslash Delta\; E\_2\; \backslash ,$ where $\backslash Delta\; E\_1$ and $\backslash Delta\; E\_2\backslash ,$ are the energy entering through $A\_1\backslash ,$ and leaving through $A\_2\backslash ,$, respectively. The energy entering through $A\_1\backslash ,$ is the sum of the kinetic energy entering, the energy entering in the form of potential gravitational energy of the fluid, the fluid thermodynamic energy entering, and the energy entering in the form of mechanical $p\backslash ,dV$ work: $\backslash Delta\; E\_1\; =\; \backslash left[\backslash frac\{1\}\{2\}\; \backslash rho\_1\; v\_1^2\; +\; \backslash phi\_1\; \backslash rho\_1\; +\; \backslash epsilon\_1\; \backslash rho\_1\; +\; p\_1\; \backslash right]\; A\_1\; v\_1\; \backslash ,\; \backslash Delta\; t$ where $\backslash phi=gh\backslash ,$, $g\backslash ,$ is acceleration due to gravity, and $h\backslash ,$ is height above a reference plane A similar expression for $\backslash Delta\; E\_2$ may easily be constructed. So now setting $0\; =\; \backslash Delta\; E\_1\; -\; \backslash Delta\; E\_2$: $0\; =\; \backslash left[\backslash frac\{1\}\{2\}\; \backslash rho\_1\; v\_1^2+\; \backslash phi\_1\; \backslash rho\_1\; +\; \backslash epsilon\_1\; \backslash rho\_1\; +\; p\_1\; \backslash right]\; A\_1\; v\_1\; \backslash ,\; \backslash Delta\; t\; -\; \backslash left[\; \backslash frac\{1\}\{2\}\; \backslash rho\_2\; v\_2^2\; +\; \backslash phi\_2\backslash rho\_2\; +\; \backslash epsilon\_2\; \backslash rho\_2\; +\; p\_2\; \backslash right]\; A\_2\; v\_2\; \backslash ,\; \backslash Delta\; t$ which can be rewritten as: $0\; =\; \backslash left[\; \backslash frac\{1\}\{2\}\; v\_1^2\; +\; \backslash phi\_1\; +\; \backslash epsilon\_1\; +\; \backslash frac\{p\_1\}\{\backslash rho\_1\}\; \backslash right]\; \backslash rho\_1\; A\_1\; v\_1\; \backslash ,\; \backslash Delta\; t\; -\; \backslash left[\; \backslash frac\{1\}\{2\}\; v\_2^2\; +\; \backslash phi\_2\; +\; \backslash epsilon\_2\; +\; \backslash frac\{p\_2\}\{\backslash rho\_2\}\; \backslash right]\; \backslash rho\_2\; A\_2\; v\_2\; \backslash ,\; \backslash Delta\; t$ Now, using the previously-obtained result from conservation of mass, this may be simplified to obtain $\backslash frac\{1\}\{2\}v^2\; +\; \backslash phi\; +\; \backslash epsilon\; +\; \backslash frac\{p\}\{\backslash rho\}\; =\; \{\backslash rm\; constant\}\; \backslash equiv\; b$ which is the Bernoulli equation for compressible flow.

Real World Application

In every-day life there are many observations that can be successfully explained by application of Bernoulli\'s principle.

• The air flowing past the top of the wing of an airplane, or the rotor blades of a helicopter, is moving very much faster than the air flowing past the under-side of the wing or rotor blade. The air pressure on the top of the wing or rotor blade is much lower than the air pressure on the under-side, and this explains the origin of the lift force generated by a wing or rotor blade to keep the airplane or helicopter in the air. The fact that the air is moving very fast over the top of the wing or rotor blade and the air pressure is very low on the top of the wing or rotor blade is an example of Bernoulli\'s principle in action, “When a stream of air flows past an airfoil, there are local changes in velocity round the airfoil, and consequently changes in static pressure, in accordance with Bernoulli’s Theorem. The distribution of pressure determines the lift, pitching moment and form drag of the airfoil, and the position of its centre of pressure.” Clancy, L.J., Aerodynamics , Section 5.5 even though Bernoulli established his famous principle over a century before the first man-made wings were used for the purpose of flight. (Bernoulli\'s principle does not explain WHY the air flows faster past the top of the wing and slower past the under-side. To understand WHY, it is helpful to understand circulation, the Kutta condition and the Kutta-Joukowski Theorem.)

• The carburetor used in many reciprocating engines contains a venturi to create a region of low pressure to draw fuel into the carburetor and mix it thoroughly with the incoming air. The low pressure in the throat of a venturi can be explained by Bernoulli\'s principle - in the narrow throat, the air is moving at its fastest speed and therefore it is at its lowest pressure.

• The velocity of a fluid can be measured using a devices such as a Venturi meter or an orifice plate, which can be placed into a pipeline to reduce the diameter of the flow. For a horizontal device, the continuity equation shows that for an incompressible fluid, the reduction in diameter will cause an increase in the fluid velocity. Subsequently Bernoulli\'s principle then shows that there must be a decrease in the pressure in the reduced diameter region. This phenomenon is known as the Venturi effect.

• The drain rate for a tank with a hole or tap at the base can be calculated directly from Bernoulli\'s equation, and is found to be proportional to the square root of the height of the fluid in the tank. This is Torricelli\'s law, showing that Torricelli\'s law is compatible with Bernoulli\'s principle.

A common misconception about wings

Some authors of introductory books about aviation and flying, when describing how wings generate lift, have advocated an explanation that avoids any reliance on Bernoulli’s principle. Two examples are given below.

Stick and Rudder

For example, in 1944 Wolfgang Langewiesche Langewiesche, Wolfgang. Stick and Rudder, McGraw-Hill (1944), New York ISBN 0-07-036240-8 wrote Stick and Rudder, an introductory text for aviation enthusiasts and student pilots. Langewiesche aimed to explain the operation of aircraft in simple terms that would be factual but easily understood by newcomers to aviation. He particularly strove to avoid concepts that were outside most people’s day-to-day experiences. “Forget Bernoulli’s Theorem” he wrote. Langewiesche, Wolfgang. Stick and Rudder, page 7 Langewiesche was a skilled aircraft pilot and instructor. He did not doubt the validity of Bernoulli’s theorem (principle), nor its applicability to aircraft, but he did recognize that any aspiring pilot need not struggle to grasp the Theorem in order to understand the basics of operation of an aircraft. Langewiesche wrote Langewiesche, Wolfgang. Stick and Rudder, page 7 “Bernoulli’s Theorem doesn’t help you the least bit in flying. While it is no doubt true, it usually merely serves to obscure to the pilot certain simpler, much more important, much more helpful facts.”

Langewiesche recognized it is important for aspiring pilots to accept that the wing of an aircraft is capable of generating lift. He also recognised that aspiring pilots need to have an understanding of Newton’s laws of motion. In writing Stick and Rudder he made it unnecessary to look further than Newton’s laws of motion to explain the forces on an aircraft. “That’s what keeps an airplane up. Newton’s Law says that if the wing pushes the air down, the air must push the wing up." Langewiesche, Wolfgang. Stick and Rudder page 9 In particular, he made it unnecessary for the reader to resort to Bernoulli’s principle to explain lift.

Understanding Flight

As a second example, in 2001 David F. Anderson and Scott Eberhardt wrote Understanding Flight, Anderson, David F., and Eberhardt, Scott. Understanding Flight, McGraw-Hill (2001), New York ISBN 0-07-136377-7 another introductory book about aviation and flying. In their Introduction, Anderson and Eberhardt acknowledge Langewiesche’s injunction “Forget Bernoulli’s Theorem”. They also say “The object of this book is to provide a clear, physical description of lift and basic aeronautical principles.” Anderson and Eberhardt provide readers with an understanding of Newton’s laws of motion, and avoid other more complex principles. In particular, they avoid any emphasis on mathematics. In their Introduction they say “It is our belief that all fundamental concepts in aeronautics can be presented in simple, physical terms, without the use of complicated mathematics. In fact, we believe that if something can only be described in complex mathematics it is not really understood. To be able to calculate something is not the same as understanding it.”

Like Langewiesche, Anderson and Eberhardt do not dispute the validity of Bernoulli’s principle. They say “This reduced pressure causes the acceleration of the air via the Bernoulli effect”. Anderson, David F., and Eberhardt, Scott. Understanding Flight, page 26

In their efforts to use simple concepts to explain the lift generated by a wing, Anderson and Eberhardt make some statements that are not consistent with other higher principles in physics and fluid dynamics. For example, they say “The acceleration of air over the top of a wing is the result of the lowered pressure and not the cause of the lowered pressure.” Further on, they say “But the lowering of the pressure above the wing is the result of the production of the downwash.” Anderson, David F., and Eberhardt, Scott. Understanding Flight, page 26 Anderson and Eberhardt attempt to explain the lift on a wing as a sequence of events, one causing a second, and the second causing a third. The acceleration of air around a wing, the lowering of air pressure, and the production of downwash all occur simultaneously. One does not cause the other. They are caused by the shape of the airfoil, its speed relative to the air, its orientation to the passing air, and even the viscosity of air. At this point, Anderson and Eberhardt may have added unnecessary complexity by implying that aviation enthusiasts and aspiring pilots need to understand which comes first, acceleration of the air, lowering of its pressure, or the production of downwash. Bernoulli’s principle says only that a change in pressure, a change in speed and a change in elevation all occur simultaneously. Bernoulli correctly avoided saying one was the cause and the others were the effect.

Like Langewiesche, Anderson and Eberhardt use the concept of downwash to explain why a wing generates lift. Anderson and Eberhardt explain downwash by referring to the Coanda effect. “This downward-traveling air is the downwash and as we will see is the source of lift on a wing. Why does the air bend around the wing? The answer is in an interesting phenomenon called the Coanda effect. The Coanda effect has to do with the bending of fluids around an object.” Anderson, David F., and Eberhardt, Scott. Understanding Flight, page 21 In Understanding Flight there is the tacit implication that if lift can be explained by the Coanda effect there is no room for any other explanation, and certainly no room for Bernoulli’s principle.

Anderson and Eberhardt also make some statements about Bernoulli’s equation and its applicability to flight. For example, in the Appendix titled Misapplications of Bernoulli’s principle Anderson and Eberhardt begin by saying “Bernoulli’s equation has mistakenly become linked to the concept of flight.”

Introductory books like Stick and Rudder, Understanding Flight and others occupy a valid place in the field of aviation because they provide newcomers with simple, easy to understand explanations that are sufficient for the newcomers to gain a basic understanding of flight and then move forward to new topics. These introductory books cater for readers for whom Bernoulli’s principle is unnecessarily complex.

Equal transit-time fallacy

Main article: Lift (force)#Equal transit-time

There is a genuine fallacy inherent in one popular explanation of the lift generated by a wing. This fallacy has become known as the "equal transit-time theory". It is well known that, when a wing is generating lift, the air travels much faster around one side of the wing than the other. To fully understand why the air travels faster around one side than the other it is helpful to understand the Kutta condition, the notion of circulation and the Kutta-Joukowski theorem but these are not simple concepts. Many authors have attempted to provide a simple explanation as to why air travels faster around one side. Some authors have pointed to the camber on most wings and suggested the air has further to travel around the cambered side of the wing than around the flat side, and to do so in equal time requires the air to move faster around the cambered side. This is not an accurate explanation of why the air moves faster around one side than the other, and it has been exposed as a fallacy.

References

See also

• Terminology in fluid dynamics
• Navier-Stokes equations – The Navier-Stokes equations for fluid flow
• Euler equations – A special case of the Navier-Stokes equation for an inviscid fluid
• Hydraulics – Applied fluid mechanics for liquids

External links

• Denver University - Bernoulli\'s equation and Pressure measurement
• Millersville University - Applications of Euler\'s Equation

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