Difference between revisions of "Intake"
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=basic theory= | =basic theory= | ||
=restrictor implications= | =restrictor implications= | ||
| − | we don't have the math extension yet, so this is gonna look wack until we do</ | + | we don't have the math extension yet, so this is gonna look wack until we do <br /> |
| − | general equation for ideal compressible gas flow:[citation needed]</ | + | general equation for ideal compressible gas flow:[citation needed]<br /> |
| − | [key for variables]</ | + | [key for variables]<br /> |
| − | <math>mdot = \frac{A*p_t}{\sqrt{T_t}}\sqrt{\frac{\gamma}{R}}M(1+\frac{\gamma-1}{2}M^2)^-\frac{\gamma+1}{2(\gamma-1}</math></ | + | <math>mdot = \frac{A*p_t}{\sqrt{T_t}}\sqrt{\frac{\gamma}{R}}M(1+\frac{\gamma-1}{2}M^2)^-\frac{\gamma+1}{2(\gamma-1}</math><br /> |
| − | when M becomes 1, the flow is considered choked. The equation becomes:</ | + | when M becomes 1, the flow is considered choked. The equation becomes:<br /> |
| − | <math>mdot = \frac{A*p_t}{\sqrt{T_t}}\sqrt{\frac{\gamma}{R}}(1+\frac{\gamma-1}{2})^-\frac{\gamma+1}{2(\gamma-1}</math></ | + | <math>mdot = \frac{A*p_t}{\sqrt{T_t}}\sqrt{\frac{\gamma}{R}}(1+\frac{\gamma-1}{2})^-\frac{\gamma+1}{2(\gamma-1}</math><br /> |
| − | With some basic assumed values at sea level, the maximum mass air flow through the restrictor can be found:</ | + | With some basic assumed values at sea level, the maximum mass air flow through the restrictor can be found:<br /> |
| − | [put table here]</ | + | [put table here]<br /> |
| − | Plugging these | + | Plugging these into the equation above yields a steady state mass flow rate of 0.074 kg air per second<br /> |
| − | If we assume an AFR of 13.1 (typical lambda for high torque for NA engines[citation needed]), and a <math>Q_LHV</ math> of 46 MJ/kg [citation needed], the mass air flow yields a power limit of 265.5 kW or 356 hp total energey output. If the thermal efficiency of the engine is assumed to be a nominal 33%, the maximum available mechanical power is 88.5 kW or 118 horsepower with 100% volumetric efficiency.</ | + | If we assume an AFR of 13.1 (typical lambda for high torque for NA engines[citation needed]), and a <math>Q_LHV</ math> of 46 MJ/kg [citation needed], the mass air flow yields a power limit of 265.5 kW or 356 hp total energey output. If the thermal efficiency of the engine is assumed to be a nominal 33%, the maximum available mechanical power is 88.5 kW or 118 horsepower with 100% volumetric efficiency.<br /> |
=throttle control= | =throttle control= | ||
Revision as of 12:03, 15 May 2020
Current/Proposed Outline:
Contents
basic theory
restrictor implications
we don't have the math extension yet, so this is gonna look wack until we do
general equation for ideal compressible gas flow:[citation needed]
[key for variables]
when M becomes 1, the flow is considered choked. The equation becomes:
Failed to parse (MathML with SVG or PNG fallback (recommended for modern browsers and accessibility tools): Invalid response ("Math extension cannot connect to Restbase.") from server "https://wikimedia.org/api/rest_v1/":): {\displaystyle mdot = \frac{A*p_t}{\sqrt{T_t}}\sqrt{\frac{\gamma}{R}}(1+\frac{\gamma-1}{2})^-\frac{\gamma+1}{2(\gamma-1}}
With some basic assumed values at sea level, the maximum mass air flow through the restrictor can be found:
[put table here]
Plugging these into the equation above yields a steady state mass flow rate of 0.074 kg air per second
If we assume an AFR of 13.1 (typical lambda for high torque for NA engines[citation needed]), and a <math>Q_LHV</ math> of 46 MJ/kg [citation needed], the mass air flow yields a power limit of 265.5 kW or 356 hp total energey output. If the thermal efficiency of the engine is assumed to be a nominal 33%, the maximum available mechanical power is 88.5 kW or 118 horsepower with 100% volumetric efficiency.
