10.4.7 == lower temperatures?!

My normal temp is now 57 from 66 C (135 from 150 F). Anyone else getting results like this? I hope this is a correct report. Temp still goes crazy under 100% cpu usage.
I also haven't heard a moo but then I've only been running the update an hour so I'm not counting my chickens on that.

I'm afraid mine still moos, even with the update. But I noticed that there was a SMC Firmware update for the 17" MacBookPro released at the same time, which is specifically designed to adjust the behaviour of the fans. Will we get one for the MacBook too I wonder?
iMac G5 Rev A   Mac OS X (10.3.9)   MacBook 2.0GHz Mac OS X (10.4.7)

Similar Messages

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  • How to account for and set the temperatur​e in testing

    The problem is this: I'm setting up an airflow resistance test and I need to account for temperature and barometric pressure. However, I don't know how to setup LabVIEW to account for these variables.

    Devont:
    Actually this issue is a fairly complex problem in aerodynamics. I am
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    purpose in a couple of wind tunnels. When you say you are setting up
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    If you are trying to measure air flow velocity through a wind tunnel
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    Also what kind of tunnel is this? Low speed subsonic (say less <100
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    Mach number is a ratio of the flow velocity to the local speed of
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    where gamma is the ratio of specific heats Cp/Cv, r is the gas
    constant, and t is the absolute temperature. Gamma is a constant up to
    about mach 4 but really starts to fall apart after that so this speed
    of sound equation becomes a lot less useful for hypersonic analysis.
    At low speeds gamma for air is approximately 1.4, r is about 287 for
    air. At STP, the speed of sound is about 340 meters/second.
    What is the scale of your tunnel? What is the density altitude of
    your tunnel? What is the fluid medium in your tunnel? (Is it regular
    air or something else?) These play into computing flow properties
    because they affect a dimensionless flow property called the Reynolds
    number which affects how the flow in the tunnel behaves.
    You will need to consider also humidity which affects the density of
    the fluid medium in your tunnel. Water vapor has a molecular weight
    of 18. Dry air (0% RH) has a molecular weight of about 28.9. The
    more water vapor you have, the lighter the sample volume of "air" will
    be. The ability of air to retain water vapor is a function of
    temperature, so a relative humidity of 100% at 0 degrees C will
    contain much less water vapor than a relative humidity of 20% at 30
    degrees C.
    Because of something called the "boundary layer" the velocity profile
    will be faster in the center of your tunnel than at the walls. It
    will resemble something like a U shape for higher Reynolds numbers and
    for very low Reynolds numbers may look more like a parabola. Reynolds
    number is computed by:
    Re=rho*V*L/mu
    where rho is the air density, V is the flow velocity, and mu is a
    property called the kinematic viscosity which is a function of
    temperature.
    The Reynolds number, like the Mach number, the Nusselt number, and a
    few other fluid dynamics properties is a dimensionless ratio. Flows
    with a similar dimensionless property should behave more or less the
    same. This is called similitude.
    Mass flow calculations first require that you know the air speed
    profile of your tunnel and then you will need to compute the density
    of the air in the tunnel and then perform an integration process to
    calculate the actual mass flow through a particular plane of interest
    in the tunnel.
    Also, even when you put a test probe into the tunnel to measure the
    flow in the tunnel, this will interfere with the free flow to a
    certain of the tunnel. To minimize this, the test probes have to be
    carefully designed and their size needs to be much smaller than the
    overall tunnel dimensions. Later when you put a test model in the
    tunnel, it and it's mounting system will also have an interference
    effect on the tunnel that has to be accounted for.
    To give a simple (perhaps an overly simple) answer to your question,
    temperature and barometric pressure will play into your problems of
    computing forces in that they affect the density of the fluid medium
    in your tunnel via the unified gas law (which is a combined expression
    of Charles and Boyles laws for perfect gases):
    PV=nRT
    or
    Pv=rT
    where rho, the density is the inverse of v, so this is sometimes
    written as:
    P/rho=rT
    This only applies for perfect gases though. A perfect gas is one
    where the constant pressure and constant volume specific heats (Cv,
    and Cp) are fixed. The hotter and more dense the fluid medium, the
    less true these equations become.
    Temperature in these equations doesn't mean the common ways that we
    ordinarily talk about temperature when cooking or talking about the
    weather. Instead of C or F, temperature in the gas law must be on an
    absolute scale such as Kelvin or Rankin. 0 degrees Kelvin or
    Rankine=-273.15 degrees C or -459.67 degrees F. One Kelvin degree=1.8
    Rankine degrees but both start at the same point of absolute zero.
    For standard atmospheric conditions (called STP for standard
    temperature and pressure), 1 cubic meter of air weighs about 1.226 kg.
    You have to calculate the density of air at non standard conditions
    by solving algebraically for the above gas law equation.
    r is called the gas constant and can be derived from the universal gas
    constant R (8314 units I can't remember of the top of my head but it
    involves kJ/kg.mole or something like) by deviding by the molecular
    weight of the gas in question. If the gas is a mixture then you will
    have to apply the partial pressures rule to come up with an averaged
    molecular weight of the mixture. Dry air contains mostly nitrogen
    which has an atomic weight of 28 (about 79%), and then oxygen (about
    20%) which has an atomic weight of 32, and the balance (about 1%)of
    inert gases (Helium, argon, krypton, etc.) which have much smaller
    atomic weights. For dry air r (small r that is) is about 287.
    If the air is not dry, then you have to account for the water vapor in
    the air by figuring out what partial pressure of water vapor is in the
    air and then performing an average between the water vapor portion and
    the other components of the air. Wator vapor only has a molecular
    weight of 18 (1 Oxygen + 2 Hydrogens=18) and so is lighter than dry
    air and tends to make the air less dense.
    The partial pressure of water vapor that can be supported in the air
    is a function of temperature that more or less grows exponentially
    with temperature. I'm sure if you search the web you can find several
    empirical equations for this. Relative Humidity (RH) is an expression
    of how much water vapor is in an air sample versus the maximum that
    can be supported at the current temperature of the air sample but what
    you really want is the partial pressure of water vapor in the air.
    There are sensors that can give this to you by measuring the
    electrical conductivity of the air. Dry air is actually a very good
    insulator, whereas water vapor decreases the insulating property of
    the air.
    All other things remaining equal, increasing the humidity will
    decrease the density of the air.
    All other things remaining equal, increasing the temperature will
    result in decreasing density while decreasing temperature will result
    in increasing density. If the temperature in your tunnel is different
    than standard then you will need to account for this.
    Tunnels generally heat up the air by the way when they accelerate the
    air through the fan and also through boundary layer friction with the
    tunnel walls. Many tunnels actually have heat exchangers to keep the
    air from getting too hot. You will need to make sure you measure the
    temperature at the same point thats you are measuring the static and
    stagnation pressures in your your tunnel so that you can account for
    its effects. Standard temperature is 15 degrees C or 59 degrees F.
    For conversion purposes, 15 degrees Celsius =288.15 degrees Kelvin= 59
    degrees Fahrenheit=518.6 degrees Rankine.
    All other things remaining equal, increasing pressure will result in
    increasing density, while decreasing pressure will result in
    decreasing density. Barometric pressure is usually given by the
    weather service as inches or millimeters of mercury or sometimes
    millibars. For conversion purposes, 29.92
    inHg=760mmHg=1000millibars=14.7 psi= 101325 Pascals pressure. If the
    pressure in your tunnel is different than standard then you will need
    to account for this.
    Depending on tunnel velocity, you will also have to consider
    stagnation versus static properties. Stagnation properties are what
    you measure if you bring the flow at a point to a complete stop, i.e.
    the kinetic (as opposed to random thermal) energy in the sample is
    completely converted thermal energy. How you do this depends on what
    speed of sample you are trying to measure and is the subject of whole
    books. Suffice it to say that at low speeds there is little
    difference between stagnation and static properties but the faster you
    go, the less resemblance they bear to one another.
    Compressibility is another issue. At low speeds air is
    incompressible, but at higher speeds v>100m/sec, compressibility
    becomes worth accounting for in your measurments.
    At higher temperatures and velocities, (high supersonic, or
    hypersonic, or high temperature >500 degrees C), the constant pressure
    and constant volume (Cp and Cv) specific heat assumptions break down
    and so does the gas law. The simplifications that can be made for
    using the ratio of Cp/Cv (called gamma) also break down because Cp and
    Cv and therefore gamma all stop being constants. Solving flow
    problems in this regime becomes much more complex requiring numerical
    models for Cp and Cv and requiring numerical (as opposed to simple
    analytical) methods to compute flow properties.
    Once you know the flow density, you can calculate air speed. For
    lower speed low temperature tunnels (low subsonic) you can use a
    simple incompressible Bernoulli equation for converting pitot-static
    pressure to air speed. At higher speeds and temperatures this depends
    on the regime (transonic, supersonic, hypersonic, etc.)
    The Bernoulli equation is simply:
    Pstagnation=Pstatic+1/2 rho * velocity^2
    For lower speed supersonic, the isentropic gas relations are sometimes
    used.
    In any event, you have to be sure to get your units right. If you use
    metric, pressure is Pascals (Newtons/m^2), rho is kg/m^3 and velocity
    is meters/sec. It's harder in U.S/U.K units because of conversions
    between slugs and pounds etc.
    Also you have to consider the concept that there will be a steady
    state average that you will measure and a transient/turbulent portion
    that will occur for each parameter that you measure (temperature,
    pressure, RH, etc.) that you will need to account for.
    Once you know the air speed and the density, you can compute their
    product - mass flow. Mass flow then can be used for other purposes
    such as calculating performance properties if you are testing a jet
    engine or propeller or something.
    Hot wire anenometers work by heating a wire and measuring the
    resistance of the wire. The faster the air flow past the wire
    filament, the more it will cool. I don't remember the equations off
    of the top of my head but I believe that there is a square rule
    involved. Hot wires work better at lower speeds than pitot-static
    sensors but both become less effective the slower you go.
    LDV's are neat, high tech toys that I haven't had a chance to work
    with yet but they measure the airspeed by measuring the doppler shift
    in the light emitted by a laser beam going through the flow, much like
    doppler (WX-88) weather radar works. They actually measure the speed
    of the air more directly than the pitot-static or hot wire methods are
    probably simpler to implement from an equations point of view but they
    are very very expensive.
    In conclusion, I know I have written a lot of stuff up here that
    probably sounds pretty intimidating with regards to solving your
    problem. It would help to eliminate some of this by telling us more
    about your test problem so that we can make the appropriate
    simplifying assumptions. Tell us more about the details.
    Douglas De Clue
    LabVIEW developer (and degreed Georgia Tech aerospace engineer)
    [email protected]
    Devont wrote in message news:<50650000000800000025530000-1027480788000@exc​hange.ni.com>...
    > The problem is this: I'm setting up an airflow resistance test and I
    > need to account for temperature and barometric pressure. However, I
    > don't know how to setup LabVIEW to account for these variables.

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