Newtonian aero calculation for a vehicle with multiple articulated surfaces.
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Classes |
| class | aero_newtonian |
| | Newtonian aerodynamic model. More...
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| struct | aero_newtonian::newtonian_aero_s |
| | Structure for storing the model for each surface.
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Functions |
| ml_matrix | newtonian_force_and_torque (const ml_matrix &normal, const ml_matrix &area, const ml_matrix &point, const ml_matrix &v, double rho, const ml_matrix &c) |
| | Newtonian lift and drag torque.
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| double | rankine_hugoniot_factor (double gamma, double m, double p_inf) |
| | Correction for newtonian flow.
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Detailed Description
Function Documentation
| ml_matrix newtonian_force_and_torque |
( |
const ml_matrix & |
normal, |
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const ml_matrix & |
area, |
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const ml_matrix & |
point, |
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const ml_matrix & |
v, |
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double |
rho, |
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const ml_matrix & |
c |
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) |
| |
Newtonian lift and drag torque.
Good above Mach 4.
- Parameters:
-
| normal | Unit normal (3xn) |
| area | Area (1xn) |
| point | Location of centroid of each point (3xn) |
| v | Velocity vector in the body frame (3x1) |
| rho | Atmospheric density |
| c | Center of mass |
- Returns:
- ml_matrix [force;torque].
| double rankine_hugoniot_factor |
( |
double |
gamma, |
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double |
m, |
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double |
p_inf |
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) |
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- Parameters:
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| gamma | Ratio of specific heats |
| m | Mach number |
| p_inf | Pressure at infinity |
- Returns:
- Maximum pressure coefficient
