The “compressor blade angle” in aircraft design refers to the angle formed between the airflow direction and the tangent to the blade surface at a specific point along the length of a compressor blade. This parameter is essential for understanding the aerodynamic performance of the compressor.Formula for Compressor Blade Angle:The blade angle (often denoted as β) can vary along the length of the compressor blade. It is typically measured at a specific point along the blade.
The formula to calculate the blade angle at a particular location is:
- β (beta) is the compressor blade angle at the specified location (measured in degrees).
- Blade Speed Tangential Component is the tangential component of the blade speed at that point.
- Inlet Air Speed Tangential Component is the tangential component of the inlet air speed at that point.
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