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Jc Propeller Design Program V. 3.11 Download

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May 14, 2021 Tarek and Christina find a good flip in Garden, CA, but Christina is worried that Tarek's penny-pinching will prevent them from making the necessary design decisions to maximize profits. As the flip goes along, Christina keeps pushing for big design to impress buyers while Tarek tries to manage the bottom line. Propeller Design: Free and OpenSource propeller design code written in Fortran. PROPDESIGN allows for the design of unducted or ducted aircraft propellers with straight or swept blades and constant or elliptical chord distributions. PROPDESIGN can be used for all altitudes covered by the U.S. Standard Atmosphere of 1976. Software Warnings 4) Indicates special care must be taken when using this element of software. 5) Indicates a special point which the user of the associate software element should be aware of. 6) Indicates a point of interest or further explanation. Objective was met by creating a computer program to design a propeller that meets user- defined aircraft performance requirements within the limitations of the motor, material, and manufacturing methods. The second author wrote a program for the described method and designed a propeller for the following case: Engine: 64.30 kW at 3000 rpm (takeoff and climb) 48.53 kW at 2700 rpm (cruise) The diameter R = 1.6 m was selected, and the cruise condition V = 200 km/h was used for the design of the propeller.

11.7.4 Dimensional Analysis

In this section we will examine propeller engines. Examples of propeller-powered vehicles are shown in Figures 11.22 and 11.23.

11.7.1 Overview of propeller performance

Each propeller blade is a rotating airfoil which produces lift and drag, and because of a (complex helical) trailing vortex system has an induced upwash and an induced downwash. Figure 11.24 shows a schematic of a propeller.

The two quantities of interest are the thrust ( )^11.1 and the torque ( ). We can write expressions for these for a small radial element ( ) on one of the blades:

where
and
It is possible to integrate the relationships as a function of with the appropriate lift and drag coefficients for the local airfoil shape, but determining the induced upwash ( ) is difficult because of the complex helical nature of the trailing vortex system. In order to learn about the details of propeller design, it is necessary to do this. However, for our purposes, we can learn about the overall performance features using the integral momentum theorem, some further approximations called ``actuator disk theory,' and dimensional analysis.

11.7.2 Application of the Integral Momentum Theorem to Propellers

The control volume shown in Figure 11.25 has been drawn far enough from the device so that the pressure is everywhere equal to a constant. This is not required, but it makes it more convenient to apply the integral momentum theorem. We will also assume that the flow outside of the propeller streamtube does not have any change in total pressure. Then since the flow is steady we apply:

Since the pressure forces everywhere are balanced, then the only force on the control volume is due to the change in momentum flux across its boundaries. Thus by inspection, we can say that
We can arrive at the same result in a step-by-step manner as we did for the jet engine example previously:

Note that the last term is identically equal to zero by conservation of mass. If the mass flow in and out of the propeller streamtube are the same (as we have defined), then the net mass flux into the rest of the control volume must also be zero.

So we have:

as we reasoned before. The power expended is equal to the power imparted to the fluid which is the change in kinetic energy of the flow as it passes through the propeller,
The propulsive power - the rate at which useful work is done - is the thrust multiplied by the flight velocity:
The propulsive efficiency is then the ratio of these two:
This is the same expression as we arrived at before for the jet engine (as you might have expected).

11.7.3 Actuator Disk Theory

To understand more about the performance of propellers, and to relate this performance to simple design parameters, we will apply actuator disk theory. We model the flow through the propeller as shown in Figure 11.26 and make the following assumptions:

Neglect rotation imparted to the flow.
Assume the Mach number is low so that the flow behaves as an incompressible fluid.
Assume the flow outside the propeller streamtube has constant stagnation pressure (no work is imparted to it).
Assume that the flow is steady. Smear out the moving blades so they are one thin steady disk that has approximately the same effect on the flow as the moving blades (the ``actuator disk').
Across the actuator disk, assume that the pressure changes discontinuously, but the velocity varies in a continuous manner.

We then take a control volume around the disk as shown in Figure 11.27.

The force, , on the disk is

so the power is
We also know that the power is
Thus we see that the velocity at the disk is
Half of the axial velocity change occurs upstream of the disk and half occurs downstream of the disk.

We can now find the pressure upstream and downstream of the disk by applying the Bernoulli equation in the regions of the flow where the pressure and velocity are varying continuously:

and

from which we can determine
We generally don't measure or control directly. Therefore, it is more useful to write our expressions in terms of flight velocity , thrust, , (which must equal drag for steady level flight) and propeller disk area, .
so
from which we can obtain an expression for the exit velocity in terms of thrust and flight velocity, which are vehicle parameters:
The other parameters of interest become
and
This is the ideal (minimum) power required to drive the propeller. In general, the actual power required would be about 15% greater than this. Lastly, the propulsive efficiency is

There are several important trends that are apparent upon consideration of these equations. We see that the propulsive efficiency is zero when the flight velocity is zero (no useful work, just a force), and tends towards one when the flight velocity increases. In practice, the propulsive efficiency typically peaks at a level of around 0.8 for a propeller before various aerodynamic effects act to decay its performance as will be shown in the following section.

11.7.4 Dimensional Analysis

We will now use dimensional analysis to arrive at a few important parameters for the design and choice of a propeller. Dimensional analysis leads to a number of coefficients which are useful for presenting performance data for propellers.

Jc Propeller Design Program V. 3.11