Very Confused Static Pressure?

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SUMMARY

This discussion focuses on calculating thrust from a propeller using propeller velocity and Bernoulli's equation. The user, Andy, outlines the formula for propeller velocity as the product of pitch and RPM. He attempts to apply Bernoulli's equation, specifically pt0 = p0 + 0.5 * r * pv^2, but struggles with determining the static pressure (p0). A key insight is that in an open airflow situation, static pressure is effectively zero.

PREREQUISITES
  • Understanding of propeller mechanics, including pitch and RPM.
  • Familiarity with Bernoulli's equation and its application in fluid dynamics.
  • Basic knowledge of pressure concepts, particularly static pressure.
  • Mathematical skills to manipulate equations and perform calculations.
NEXT STEPS
  • Research the application of Bernoulli's equation in open airflow scenarios.
  • Study the relationship between propeller pitch, RPM, and thrust generation.
  • Learn about static pressure measurement techniques in fluid dynamics.
  • Explore advanced topics in fluid mechanics related to propeller efficiency.
USEFUL FOR

Aerospace engineers, mechanical engineers, and hobbyists involved in propeller design and performance analysis will benefit from this discussion.

Gibbon
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Hi, I am trying to calculate as best but simply as i can the (approx) thrust from a propeller..

and my research shows i have to calculate:

prop velocity(pv) = pitch * rpm

with pv i can then use Bernoulli's equation to calulate the pressure and multiply it by the propeller surface area to give me thrust.

So ... pt0 = p0 + .5 * r * pv ^2

that equation should give me thrust.. But. p0 is apparently "Static Pressure".. and i cannot for the life of me work out how to calculate static pressure.

Hope you can help, my maths isn't all upto scratch so be kind! :)

Thanks
Andy
 
Physics news on Phys.org
In an open airflow situation (no ducting), there is no static pressure.
 

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