REFLECTOR: Air pressure question...

[Scott Derrick]

No, Sid gave the formula to calculate the pitot pressure at any alltitude.

Neal posted a chart of the static pressure at different altitudes..

Put them together and your free to calculate any Q at any airspeed at 
any altitude.

Scott

Richard Riley wrote:

> No, he just answered what the static air pressure would be.  Like, at 
> sea level it's 14.8 PSI, at 20,000 feet it's 6.7psi.
>
> Hiroo is (I think) asking about the "Q" - the pitot pressure at 
> different airspeeds.
>
> Q is .5 times the density of the air times velocity squared.
>
> I'm sure there must be a java calculator somewhere on the web, but I 
> can't find one.
>
> At 08:15 AM 6/17/05, you wrote:
>
>> Didn't Sid just answer that?
>>
>> Hiroo Umeno wrote:
>>
>>> Great.  This really helps.  How about the airspeeds?  Do you guys 
>>> know what the pressure differential be at say, 250KIAS?
>>>
>>>
>>>
>>> ------------------------------------------------------------------------ 
>>>
>>>
>>> *From:* reflector-bounces at tvbf.org 
>>> [mailto:reflector-bounces at tvbf.org] *On Behalf Of *Neal Hoffoss
>>> *Sent:* Thursday, June 16, 2005 10:18 PM
>>> *To:* Velocity Aircraft Owners and Builders list
>>> *Subject:* Re: REFLECTOR: Air pressure question...
>>>
>>>
>>>
>>> Here's the air pressure at different altitudes.  As for the delta 
>>> PSI, my physics is probably rustier than yours!
>>>
>>>
>>>
>>> 0
>>>
>>>
>>>
>>> 14.696
>>>
>>> 500
>>>
>>>
>>>
>>> 14.43
>>>
>>> 1000
>>>
>>>
>>>
>>> 14.16
>>>
>>> 1500
>>>
>>>
>>>
>>> 13.91
>>>
>>> 2000
>>>
>>>
>>>
>>> 13.66
>>>
>>> 2500
>>>
>>>
>>>
>>> 13.41
>>>
>>> 3000
>>>
>>>
>>>
>>> 13.17
>>>
>>> 3500
>>>
>>>
>>>
>>> 12.93
>>>
>>> 4000
>>>
>>>
>>>
>>> 12.69
>>>
>>> 4500
>>>
>>>
>>>
>>> 12.46
>>>
>>> 5000
>>>
>>>
>>>
>>> 12.23
>>>
>>> 6000
>>>
>>>
>>>
>>> 11.78
>>>
>>> 7000
>>>
>>>
>>>
>>> 11.34
>>>
>>> 8000
>>>
>>>
>>>
>>> 10.91
>>>
>>> 9000
>>>
>>>
>>>
>>> 10.5
>>>
>>> 10,000
>>>
>>>
>>>
>>> 10.1
>>>
>>> 15,000
>>>
>>>
>>>
>>> 8.29
>>>
>>> 20,000
>>>
>>>
>>>
>>> 6.76
>>>
>>> 25,000
>>>
>>>
>>>
>>> 5.46
>>>
>>>
>>>
>>> ------------------------------------------------------------------------ 
>>>
>>>
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>
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>
>