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In thermodynamics and fluid mechanics, compressibility is a measure of the relative volume change of a fluid or solid as a response to a pressure (or mean stress) change.

- $beta=-frac\{1\}\{V\}frac\{partial\; V\}\{partial\; p\}$

where V is volume and p is pressure. The above statement is incomplete, because for any object or system the magnitude of the compressibility depends strongly on whether the process is adiabatic or isothermal. Accordingly we define the isothermal compressibility as:

- $beta\_T=-frac\{1\}\{V\}left(frac\{partial\; V\}\{partial\; p\}right)\_T$

where the subscript T indicates that the partial differential is to be taken at constant temperature. The adiabatic compressibility as:

- $beta\_S=-frac\{1\}\{V\}left(frac\{partial\; V\}\{partial\; p\}right)\_S$

where S is entropy. For a solid, the distinction between the two is usually negligible.

The inverse of the compressibility is called the bulk modulus, often denoted K (sometimes B). That page also contains some examples for different materials.

The term "compressibility" is also used in thermodynamics to describe the deviance in the thermodynamic properties of a real gas from those expected from an ideal gas. The compressibility factor is defined as

- $Z=frac\{p\; tilde\{V\}\}\{R\; T\}$

- $p\; =\; \{RTover\{tilde\{V\}\}\}$

Z can, in general, be either greater or less than unity for a real gas.

The deviation from ideal gas behavior tends to become particularly significant (or, equivalently, the compressibility factor strays far from unity) near the critical point, or in the case of high pressure or low temperature. In these cases, a generalized compressibility chart or an alternative equation of state better suited to the problem must be utilized to produce accurate results.

A related situation occurs in hypersonic aerodynamics, where dissociation causes an increase in the “notational” molar volume, because a mole of Oxygen, as O2, becomes 2 moles of monatomic Oxygen and N2 similarly dissociates to 2*N. Since this occurs dynamically as air flows over the aerospace object, it is convenient to alter Z, defined for an initial 30 gram “mole” of air, rather than track the varying mean molecular weight, millisecond by millisecond. This pressure dependent transition occurs for atmospheric Oxygen in the 2500K to 4000K temperature range, and in the 5000K to 10,000K range for Nitrogen.

In transition regions, where this pressure dependent dissociation is incomplete, both beta (the volume/pressure differential ratio) and the differential, constant pressure heat capacity will greatly increase.

For moderate pressures, above 10,000K the gas further dissociates into free electrons and ions. Z for the resulting plasma can similarly be computed for a mole of initial air, producing values between 2 and 4 for partially or singly ionized gas. Each dissociation absorbs a great deal of energy in a reversible process and this greatly reduces the thermodynamic temperature of hypersonic gas decelerated near the aerospace object. Ions or free radicals transported to the object surface by diffusion may release this extra (non thermal) energy if the surface catalyzes the slower recombination process.

The isothermal compressibility is related to the isentropic (or adiabatic) compressibility by the relation,

- $beta\_S\; =\; beta\_T\; -\; frac\{alpha^2\; T\}\{rho\; c\_p\}$

via Maxwell's relations. More simply stated,

- $frac\{beta\_T\}\{beta\_S\}\; =\; gamma$

where,

- $gamma\; !$ is the heat capacity ratio. See here for a derivation.

Material | β (m²/N) |
---|---|

Plastic clay | 2 – 2.6 |

Stiff clay | 2.6 – 1.3 |

Medium-hard clay | 1.3 – 6.9 |

Loose sand | 1 – 5.2 |

Dense sand | 2 – 1.3 |

Dense, sandy gravel | 1 – 5.2 |

Rock, fissured | 6.9 – 3.3 |

Rock, sound | <3.3 |

Water at 25 °C (undrained) | 4.6 |

It is an important concept in geotechnical engineering in the design of certain structural foundations. For example, the construction of high-rise structures over underlying layers of highly compressible bay mud poses a considerable design constraint, and often leads to use of driven piles or other innovative techniques.

Some of the minor effects include changes to the airflow that lead to problems in control. For instance, the P-38 Lightning with its thick high-lift wing had a particular problem in high-speed dives that led to a nose-down condition. Pilots would enter dives, and then find that they could no longer control the plane, which continued to nose over until it crashed. Adding a "dive flap" beneath the wing altered the center of pressure distribution so that the wing would not lose its lift. This fixed the problem.

A similar problem affected some models of the Supermarine Spitfire. At high speeds the ailerons could apply more torque than the Spitfire's thin wings could handle, and the entire wing would twist in the opposite direction. This meant that the plane would roll in the direction opposite to that which the pilot intended, and led to a number of accidents. Earlier models weren't fast enough for this to be a problem, and so it wasn't noticed until later model Spitfires like the Mk.IX started to appear. This was mitigated by adding considerable torsional rigidity to the wings, and was wholly cured when the Mk.XIV was introduced.

The Messerschmitt Bf 109 and Mitsubishi Zero had the exact opposite problem in which the controls became ineffective. At higher speeds the pilot simply couldn't move the controls because there was too much airflow over the control surfaces. The planes would become difficult to maneuver, and at high enough speeds aircraft without this problem could out-turn them.

Finally, another common problem that fits into this category is flutter. At some speeds the airflow over the control surfaces will become turbulent, and the controls will start to flutter. If the speed of the fluttering is close to a harmonic of the control's movement, the resonance could break the control off completely. This was a serious problem on the Zero. When problems with poor control at high speed were first encountered, they were addressed by designing a new style of control surface with more power. However this introduced a new resonant mode, and a number of planes were lost before this was discovered.

All of these effects are often mentioned in conjunction with the term "compressibility", but in a manner of speaking, they are incorrectly used. From a strictly aerodynamic point of view, the term should refer only to those side-effects arising as a result of the changes in airflow from an incompressible fluid (similar in effect to water) to a compressible fluid (acting as a gas) as the speed of sound is approached. There are two effects in particular, wave drag and critical mach.

Wave drag is a sudden rise in drag on the aircraft, caused by air building up in front of it. At lower speeds this air has time to "get out of the way", guided by the air in front of it that is in contact with the aircraft. But at the speed of sound this can no longer happen, and the air which was previously following the streamline around the aircraft now hits it directly. The amount of power needed to overcome this effect is considerable. The critical mach is the speed at which some of the air passing over the aircraft's wing becomes supersonic.

At the speed of sound the way that lift is generated changes dramatically, from being dominated by Bernoulli's principle to forces generated by shock waves. Since the air on the top of the wing is traveling faster than on the bottom, due to Bernoulli effect, at speeds close to the speed of sound the air on the top of the wing will be accelerated to supersonic. When this happens the distribution of lift changes dramatically, typically causing a powerful nose-down trim. Since the aircraft normally approached these speeds only in a dive, pilots would report the aircraft attempting to nose over into the ground.

In hypersonic aerodynamics, dissociation causes an increase in the “notational” molar volume (a mole of Oxygen, as O2, becomes 2 moles of monatomic Oxygen and N2 similarly dissociates to 2*N). This pressure dependent transition occurs for atmospheric Oxygen in the 2500K to 4000K temperature range, and in the 5000K to 10,000K range for Nitrogen.

Dissociation absorbs a great deal of energy in a reversible process. This greatly reduces the thermodynamic temperature of hypersonic gas decelerated near an aerospace vehicle. In transition regions, where this pressure dependent dissociation is incomplete, both the differential, constant pressure heat capacity and beta (the volume/pressure differential ratio) will greatly increase. The later has a pronounced effect on vehicle aerodynamics including stability.

- Poisson ratio
- Mach number
- Prandtl-Glauert singularity, associated with supersonic flight.
- Shear strength

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Last updated on Wednesday September 03, 2008 at 14:28:46 PDT (GMT -0700)

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This article is licensed under the GNU Free Documentation License.

Last updated on Wednesday September 03, 2008 at 14:28:46 PDT (GMT -0700)

View this article at Wikipedia.org - Edit this article at Wikipedia.org - Donate to the Wikimedia Foundation

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