3d Shape with lowest drag coefficient subsonic ground level

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SUMMARY

The optimal shape for achieving the lowest drag coefficient at ground level and subsonic speeds (0-150 kph) is a symmetrical airfoil, specifically the NACA 0021 airfoil. The dimensions specified for the motorcycle are width of 60 cm, height of 120 cm, and length of 220 cm. While a teardrop shape is suggested as close to ideal, truncating the tail is confirmed to increase drag. The NACA 0021 airfoil, when stretched to meet the required dimensions, is expected to achieve a drag coefficient below 0.1, enabling speeds of approximately 200 kph at 10 kW.

PREREQUISITES
  • Understanding of aerodynamic principles
  • Familiarity with airfoil shapes and their characteristics
  • Knowledge of drag coefficient and its significance in vehicle design
  • Experience with computational fluid dynamics (CFD) tools for testing shapes
NEXT STEPS
  • Research the characteristics of the NACA 0021 airfoil and its applications
  • Explore the use of airfoiltools.com for airfoil design and analysis
  • Learn about computational fluid dynamics (CFD) simulations for drag coefficient testing
  • Investigate alternative airfoil shapes that may offer lower drag coefficients
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Engineers, motorcycle designers, and aerodynamicists interested in optimizing vehicle shapes for performance and efficiency will benefit from this discussion.

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Hello,

What shape has the lowest drag coefficient at ground level and at subsonic speeds (0-150kph) with the following dimensions?

Width 60cm (at 45%)
Height 120cm (at 45%)
Length 220cm

These dimensions will fit my motorcycle (not too narrow and not too long).

I am thinking it would be a symmetrical airfoil with a truncated tail but I do not know for sure. That is why I am asking.

The shape will have 10-20cm ground clearance.

Thank you for your time, this stuff is way over my head.
 
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A teardrop shape would likely be pretty close to ideal. Truncating the tail would likely increase drag.
 
I'd have to agree with you there.

I have been looking at airfoiltools.com.

Stretching the naca 0021 airofoil to 128.7% gives the required 60cm thickness with a 220cm chord. However the widest point is at 30% length not 45% length. It is impossible to change this. Also the changed airfoil cannot be tested to determine it's drag coefficient.

The same naca0021 airfoil would be stretched vertically to double the thickness to reach the required height of 120cm. However this is impossible to create and impossible to test.

Considering that a naca0021 airfoil with a fineness ratio of 3:1 is perfect in the air and 5:1 ratio on the ground I definitely want to get as close to the latter ratio.

Using the perfect shape of the naca 0021 airfoil I should be able to achieve sub 0.1 drag coefficient and reach speeds of around 200kph at 10kw.

It is unknown if there is a shape better than the naca 0021.