It is quite the in-depth article for you folks who had a lot of questions. I'm glad you appreciate it. In theory it seems right, but it is not right. This will maximize your *static* thrust while giving you a very steep negative slope on your dynamic thrust plot (see Figure 2). (rough guess is ok). The theory does not include secondary effects such as 3-D flow velocities induced on the propeller by the shed tip Also, it helps to validate my equation and your point about the 2-points thing.So, it looks like your equation at the bottom of your statement is off, but your idea is correct. 1 Overview of propeller performance. …(continued from previous comment)Now, as you stated, you have 2 points, where one is the static thrust (x = 0 and y = static thrust) and one is the zero-thrust airspeed (x = zero-thrust airspeed = pitch speed, and y = 0). Once I get more wind tunnel data (or flight test data) that I can use to find the x-intersect, I can come up with another empirical correction factor and get my equation to be more accurate for dynamic thrust too. efficiency for a relatively simple propeller design using standard linearised aerofoil section data. Hi, my concern is because i got my velocity from fight test when running at full throttle. I still have some questions about it myself but haven't had time to re-attack the problem for the last several years. In other words: I have tested prop 8x4 and the plot for Static Thrust vs RPM is the same as ideal prop 6.4x3.2 using theoretical formula (mass flow x Vp). The back prop is a 3 blade rc boat prop with 3"x5.5. Our static thrusts for our chosen prop are 247 grams at 50% throttle and 520 grams at 100% throttle. Calculate a new drag based on this velocity. 1) "but im not arriving at the right solution. --For fast flying you want a small diameter prop with a large pitch, and a high kv motor. Honestly I don't have the answer right now for how to get this calculation to work for a 3-bladed prop. The open-water thrust. F = [m dot * V]e - [m dot * V]0. To correct your equation, simply look back at your original equation: Thrust = m_dot*(Vp-Vo). A poorly chosen propeller-engine combination will at best result in an aircraft that does not meet the performance requirements outlined by the aircraft designer. Please help me out in this.And also i want to know if we could somehow use dynamic thrust to calculate take-off distance of any rc model plane . A 2-bladed prop with the same pitch and diameter and at the same RPM might produce an exit velocity of 0.7Ve_max (1.4x [the “x” is read as “times” here] the exit velocity of a 1-bladed prop), a 3-bladed prop might do 0.8Ve_max (1.6x that of a 1-bladed prop), and a 4-bladed prop might produce 0.85Ve_max (1.7x that of a 1-bladed prop). @Smiling Buddha: Pitch is the distance -RELATED TO AIR- travelled by the propeller in one rotation. The reason thrust (or lift) scaling is nonlinear is because the blades must occupy a finite amount of space, equal to the frontal, circular area of the spinning propeller, and the more area the blades occupy, the less area that air has to pass through the blades. Cheers! This produces a set of non-linear equations that can be solved by iteration for each blade section. Quadcopter thrust calculator. For the first iteration, Drag = 0 since the vehicle is not moving. Ok, so let’s call this frontal area the propeller “disc.” The area of the disc is equal to pi*(d^2)/4, where d is the diameter of the propeller. This lecture includes aerodynamic propeller principle of operation along with a highly accurate propeller (static & net) thrust formula calculation. It looks like you are calculating mass of air per second * (Vp^2 – VpVo)*(d/3.29546.pitch)^1.5 Where the term (d/3.29546*pitch)^1.5 comes from? Click here to download Propeller MATLAB script: Propel.m, Axial and Angular Flow Conservation of Momentum. I fly a lot of RC airplanes.

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