Predicting transition from laminar to turbulent flow over a surface using mode-shape parameters
View Patent ↗In accordance with embodiments disclosed herein, there are provided methods, systems, and apparatuses for predicting whether a point on a computer-generated aircraft or vehicle surface is adjacent to laminar or turbulent flow is made using a transition prediction technique. A plurality of boundary-layer properties at the point are obtained from a steady-state solution of a fluid flow in a region adjacent to the point. Included in the list of boundary-layer properties are computed coefficients or weights of mode shapes that describe the boundary-layer profiles. A plurality of instability modes are obtained, each defined by one or more mode parameters. A vector of regressor weights is obtained for the known instability growth rates in a training dataset. For each instability mode in the plurality of instability modes, a covariance vector is determined, which is the covariance of a predicted local growth rate with the known instability growth rates. Each covariance vector is used with the vector of regressor weights to determine a predicted local growth rate at the point. Based on the predicted local growth rates, an n-factor envelope at the point is determined.
1. A computer-implemented method for predicting a flow condition for a transition point along a computer-generated surface, the method comprising:
obtaining a set of boundary-layer properties associated with a simulated fluid flow over the computer generated surface;
obtaining one or more mode parameters associated with an instability mode;
obtaining a vector of values associated with a set of known instability growth rates of a training set;
determining a covariance vector including a covariance of a predicted local growth rate for the transition point with respect to each of the set of known instability growth rates;
determining the predicted local growth rate at the transition point using the vector of values and the covariance vector; and
determining an n-factor envelope at the transition point for the instability mode using the predicted local growth rate, wherein the n-factor envelope is indicative of whether the transition point is adjacent to laminar or turbulent flow.
2. The computer-implemented method of claim 1 , wherein the set of boundary-layer properties includes a flow velocity and a temperature profile for the simulated fluid flow proximate to the transition point.
3. The computer-implemented method of claim 1 , wherein the set of boundary-layer properties includes a set of coefficient weights that corresponds to one or more mode-based profiles.
4. The computer-implemented method of claim 3 , wherein the one or more mode-based profiles are derived using a singular value decomposition.
5. The computer-implemented method of claim 1 , wherein:
the computer-generated surface represents a surface of a wing; and
the method further comprises determining whether the simulated fluid flow at the transition point is turbulent or laminar based on whether the n-factor envelope at the transition point exceeds a threshold value.
6. The computer-implemented method of claim 5 , wherein:
in response to the n-factor envelope at the transition point exceeding the threshold value, determining that the transition point is associated with turbulent flow; and
in response to the n-factor envelope at the transition point not exceeding the threshold value, determining that the transition point is associated with laminar flow.
7. The computer-implemented method of claim 1 , wherein:
the instability mode is a first instability mode of a plurality of instability modes; and
the plurality of instability modes include one or more of: a Tollmien-Schlichting (TS) wave instability mode or a crossflow vortices mode.
8. The computer-implemented method of claim 1 , wherein the vector of values is a vector of regressor weights of the set of known instability growth rates.
9. The computer-implemented method of claim 8 , wherein:
the vector of regressor weights is based on a covariance matrix;
the covariance matrix includes elements that are a covariance of a first known instability mode with respect to a second known instability mode; and
the covariance of the first known instability mode with respect to the second known instability mode is based on a distance between a first and a second training input vector associated with a first and a second known instability growth rate, respectively.
10. The computer-implemented method of claim 9 , wherein the covariance matrix and the covariance vector are based on a squared exponential covariance function.
11. A system for predicting a transition from laminar to turbulent flow over a computer-generated surface, the system comprising:
a display;
a processor operably coupled to the display; and
computer-readable memory storing computer-executable instructions for execution on the processor, the computer-executable instructions including instructions for:
obtaining a set of flow properties associated with a simulated fluid flow over the computer-generated surface, the set of flow properties including a set of coefficient weights;
obtaining one or more mode parameters associated with an instability mode;
obtaining a vector of regressor weights associated with a set of known instability growth rates;
determining a covariance vector including a covariance of a predicted local growth rate for a point along the computer-generated surface with respect to each of the set of known instability growth rates;
determining the predicted local growth rate at the point using the vector of regressor weights and the covariance vector; and
determining an n-factor envelope at the point for the instability mode using the predicted local growth rate, wherein the n-factor envelope is indicative of whether the point is adjacent to laminar or turbulent flow.
12. The system of claim 11 , wherein:
the set of coefficient weights corresponds to one or more mode-based profiles; and
the one or more mode-based profiles are derived using a singular value decomposition.
13. The system of claim 11 , wherein:
the set of known instability growth rates is part of a training dataset;
the training dataset includes a training input vector associated with each known instability growth rate of the set of known instability growth rates;
each training input vector includes training boundary layer properties and at least one training instability mode parameter;
the vector of regressor weights is based on a covariance matrix that has elements that are the covariance of a first known instability mode with respect to a second known instability mode; and
the covariance of the first known instability mode with respect to the second known instability mode is based on a distance between a first and a second training input vector associated a first and a second known instability growth rate, respectively.
14. The system of claim 11 , wherein:
the computer-generated surface represents a surface of an airplane;
the instructions further comprise instructions for determining whether the simulated fluid flow at the point is turbulent or laminar based on whether the n-factor envelope at the point exceeds a threshold value;
in response to the n-factor envelope at the point exceeding the threshold value, determining that the transition point is associated with turbulent flow; and
in response to the n-factor envelope at the point not exceeding the threshold value, determining that the transition point is associated with laminar flow.
15. A computer system comprising:
computer memory storing computer-executable instructions;
a processor configured to execute the computer-executable instructions, the computer-executable instructions for:
obtaining a set of flow properties associated with a simulated fluid flow over a computer-generated surface, the set of flow properties including a set of coefficient weights;
obtaining one or more mode parameters associated with each of a set of instability modes;
obtaining a vector of regressor weights associated with a set of known instability growth rates;
determining a covariance vector including a covariance of a predicted local growth rate for a point along the computer-generated surface with respect to each of the set of known instability growth rates;
determining the predicted local growth rate at the point using the vector of regressor weights and the covariance vector; and
determining an n-factor envelope at the point for an instability mode using the predicted local growth rate, wherein the n-factor envelope is indicative of whether the point is adjacent to laminar or turbulent flow.
16. The computer system of claim 15 , wherein:
the set of coefficient weights corresponds to one or more mode-based profiles; and
the one or more mode-based profiles are derived using a singular value decomposition.
17. The computer system of claim 15 , wherein:
the computer-generated surface represents a surface of an aircraft;
the set of flow properties is associated with a supersonic flight condition; and
the computer-readable instructions further comprise instructions for determining if a shock wave is predicted to occur along the surface of the aircraft.
18. The computer system of claim 15 , further comprising instructions for:
determining if the n-factor envelope exceeds a threshold for the point; and,
in response to the n-factor envelope exceeding the threshold, determining that the point is adjacent to turbulent flow.
19. The computer system of claim 15 , wherein:
the set of known instability growth rates is part of a training dataset; and
the training dataset is generated with linear stability theory (LST) model analysis.
20. The computer system of claim 15 , wherein:
the predicted local growth rate is associated with the set of flow properties and a mode parameter of the one or more mode parameters; and
the covariance of the predicted local growth rate with respect to a known instability growth rate is based on a distance from a flow property of the set of flow properties and the mode parameter to a training input vector associated with the known instability growth rate.