Discover the Formula for Calculating Static Thrust and RPM Ratio

In summary, static thrust is the force produced by an engine or propeller when the aircraft is not moving. It is an important factor in determining an aircraft's acceleration and climb performance. Static thrust is calculated by multiplying the mass flow rate of air by the difference between entry and exit velocities. Various factors, such as engine/propeller design, air density, and temperature, can affect static thrust. To increase static thrust, one can increase the mass flow rate or velocity difference, as well as optimize the engine/propeller design. Dynamic thrust, on the other hand, takes into account the effects of drag and velocity while the aircraft is in motion.
  • #1
rubai
3
0
i want to know the relation between thrust/rpm. what is the formula to calculate it?
 
Physics news on Phys.org
  • #2
You can't directly calculate thrust if all you know is RPMs.
 
  • #3
If angle of attack and area of rotor blade is fixed how can i calculate it. could you please tell me the calculation of it for fixed parameters.
 
  • #4
T=ct half row v square s
 
  • #5


I would like to inform you that the formula for calculating static thrust and RPM ratio is as follows:

Static Thrust/RPM = (2 x pi x pitch x diameter x (air density)^2 x RPM^2)/(4 x pitch^2 x (air density)^2 x RPM^2 + diameter^2 x (air density)^2 x RPM^2)

This formula takes into account the pitch (the distance a propeller would move forward in one revolution), diameter (the length from one end of the propeller blade to the other), and air density (the mass of air per unit volume) to calculate the relationship between thrust and RPM.

The resulting value is a ratio that represents the amount of thrust produced per unit of RPM. This ratio can be used to compare the performance of different propellers or to determine the optimal RPM for a given thrust requirement.

It is important to note that this formula is only applicable for calculating static thrust, which is the thrust produced by a propeller when the aircraft is stationary. In dynamic flight, other factors such as airspeed and angle of attack also play a significant role in determining thrust.

I hope this information helps to clarify the relationship between thrust and RPM and the formula used to calculate it. As always, further research and experimentation may lead to refinements or modifications of this formula.
 

What is static thrust and why is it important?

Static thrust is the measure of the force produced by an engine or propeller when the aircraft is not moving. It is important because it determines the acceleration and climb performance of an aircraft.

How is static thrust calculated?

Static thrust is calculated by multiplying the mass flow rate of air through the engine or propeller by the difference between the entry and exit velocities. This can be calculated using the following equation: Static Thrust = Mass Flow Rate * (Exit Velocity - Entry Velocity)

What factors affect static thrust?

The factors that affect static thrust include the design and size of the engine or propeller, air density, and ambient temperature. Other factors such as altitude, humidity, and engine/propeller efficiency can also have an impact on static thrust.

How can static thrust be increased?

Static thrust can be increased by increasing the mass flow rate of air through the engine or propeller, increasing the difference between entry and exit velocities, and optimizing the design and efficiency of the engine or propeller. Other methods such as using afterburners or adding additional engines can also increase static thrust.

What is the difference between static thrust and dynamic thrust?

Static thrust is the force produced by an engine or propeller when the aircraft is not moving, while dynamic thrust is the force produced when the aircraft is in motion. Dynamic thrust takes into account the effects of drag and the aircraft's velocity, while static thrust does not.

Similar threads

Propeller blade lift distribution for best thrust/power ratio?
    • Aerospace Engineering
Replies
7
Views
2K
Rocket thrust equation in under-expanded nozzle
    • Aerospace Engineering
Replies
2
Views
2K
How calculate lift/drag using static pressure taps in wind tunnel test?
    • Aerospace Engineering
Replies
9
Views
2K
Centrifugal Compressor: Absolute Velocity Calculation
    • Aerospace Engineering
Replies
5
Views
506
Optimizing Thrust and Operation Time for a CO2-Powered Rocket Torpedo Design
    • Aerospace Engineering
Replies
7
Views
2K
Relating propeller thrust, power, and rpm together
    • Aerospace Engineering
Replies
8
Views
4K
Propeller with bell lift distribution has best thrust/power ratio?
    • Aerospace Engineering
Replies
2
Views
1K
Prop disc thrust uniformity in turns vs wing position
    • Aerospace Engineering
Replies
6
Views
2K
Bi-propellant Liquid Fuel Engine Pressures Before Thrust Chamber
    • Aerospace Engineering
Replies
2
Views
2K
Propeller thrust with backwards air flow
    • Aerospace Engineering
Replies
3
Views
1K

Hot Threads

Recent Insights

Back
Top