What is the best design for cooling vents on a Sukhoi radial engine?

In summary, the individual is seeking advice on the design of cooling vents and louvres for a Sukhoi RC plane with a 76 inch span and 37cc petrol engine. They are specifically looking for the optimum size and angle for a single flat plate versus 2 or 3 louvres and the best spacing. Suggestions for experimentation and instrumentation are also given.
  • #1
Sopwith1
1
0
Advice needed please with the design of cooling vents, louvres on the cowling of a radial engine. Plane is a Sukhoi, as per vid links below, 76 inch span 37cc petrol engined radio control. Cooling will be from cutouts in the cowl approx 20 x 80 mm with a flat plate louvre at the leading edge. Most flying will be low airspeed so airflow wil be mainly propwash.

What I would like your help with is the optimum size(how much protruding from cowl) and angle for a single flat plate, and how much more effective would this be if there was 2 or 3 louvres. If using 2 or more what is the best spacing.
Very much how long is a piece of string I know, but a ball park idea would be much appreciated. I've attached a couple of links showing the plane and style of flying.
many thanks
Robin :smile:

http://video.google.com/googleplayer.swf?docid=4995237916930599540&hl=en&fs=true

 
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  • #2
Sopwith1,

A belated welcome to PF!

That is a brute of an RC plane! And whoever is piloting it is very skillful...

As far as an approach to answering your question, I would suggest experimentation. If cowls are cheap and available, louver one, mount it and fly the plane. To determine its cooling performance, instrument the plane with thermistors or thermocouples on the exhausts and feed the signals to an on-board memory chip. Some cheap home digital thermostat might be adapted to convert the analog signal to digital data. After a test flight, retreive and analyze the data to see if the louvers did the job. If not, change the louvering and try again.

Heck, with the power that plane has, you could probably mount a transmitter and get real-time data during a test flight.

And if that sounds crazy, what about servo-driven dampers on the louvers controlled by the thermocouple signals?
 
  • #3



I would approach this problem by first considering the basic principles of heat transfer and flow dynamics. In order to effectively cool a radial engine, we need to ensure that there is sufficient airflow over the engine to remove the heat generated during operation. This can be achieved by designing the cooling vents in a way that maximizes the amount of air passing through them.

Based on the information provided, it seems that the proposed design involves using cutouts in the cowl with a flat plate louvre at the leading edge. The size and angle of the louvre, as well as the number and spacing of the vents, will play a crucial role in determining the effectiveness of this cooling system.

For the size and angle of the louvre, it would be beneficial to conduct some simulations or experiments to determine the optimal values. However, as a general rule, the angle of the louvre should be such that it allows air to enter the cowl and flow over the engine, while also preventing any debris from entering. As for the size, it should be large enough to allow sufficient air to pass through, but not so large that it creates excessive drag.

In terms of the number and spacing of the vents, it would be best to have multiple vents rather than a single one. This will allow for more even distribution of airflow over the engine. The exact spacing will depend on the size and shape of the cowl, but it should be enough to ensure that there are no stagnant areas where air cannot flow.

Additionally, it would be helpful to consider the placement of the vents in relation to the propeller. Since most of the airflow will be generated by the propwash, it would be beneficial to have the vents positioned in a way that maximizes this effect.

In conclusion, the best design for cooling vents on a Sukhoi radial engine would involve multiple vents with an appropriate size and angle, strategically placed in relation to the propeller. It would also be beneficial to conduct further experiments or simulations to fine-tune the design for optimal cooling performance.
 

1. How does an aircraft engine stay cool during flight?

An aircraft engine stays cool during flight through a combination of air cooling and liquid cooling methods. The majority of aircraft engines use air cooling, which involves directing cool air from outside the plane into the engine to dissipate heat. Liquid cooling, on the other hand, involves circulating a liquid coolant through the engine to absorb heat and then transferring it outside the aircraft.

2. What are the consequences of inadequate cooling in an aircraft engine?

Inadequate cooling in an aircraft engine can result in overheating, which can cause the engine to stall or fail. This can be dangerous for the aircraft and its passengers, and can even lead to a crash. Additionally, overheating can also cause damage to engine components, leading to costly repairs.

3. How do engineers design aircraft engine cooling systems?

Engineers use a combination of computer simulations, wind tunnel testing, and real-world flight testing to design aircraft engine cooling systems. They consider factors such as engine size and power, flight speed and altitude, and environmental conditions to determine the most efficient and effective cooling system for a particular aircraft.

4. How do aircraft engines cool down after landing?

After landing, aircraft engines continue to run for a short period of time to cool down. This is known as the "cool down" phase and is necessary to prevent thermal stress and damage to the engine components. During this phase, the engine is kept at idle power and the aircraft's speed is kept low to allow for proper cooling.

5. How do extreme temperatures affect aircraft engine cooling?

Extreme temperatures can have a significant impact on aircraft engine cooling. In very hot temperatures, the air entering the engine may not be cool enough to effectively dissipate heat, leading to overheating. In very cold temperatures, the engine may not receive enough air flow to prevent ice formation, which can also affect cooling. Engineers must take these factors into account when designing cooling systems for aircraft engines.

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