Abstract
An existing transition prediction method for attached, two-dimensional, incompressible boundary layers based on linear stability analysis is extended to separated, two-dimensional, incompressible boundary layers such as those found in laminar (transitional) separation bubbles. It is shown why the present method, which tracks the growth of disturbances at many different frequencies, is more accurate than the so-called envelope methods. Reliance on a data base of pre-calculated stability characteristics of known velocity profiles makes this method much faster than traditional stability calculations of similar accuracy. The Falkner-Skan self-similar profiles are used for attached flow and a new, very general family of profiles is used for separated flow. Comparisons with measured transition locations inside the bubble show good agreement over the range of chord Reynolds numbers and airfoil angles of attack of interest.
Original language | English (US) |
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State | Published - 1991 |
Event | 9th Applied Aerodynamics Conference, 1991 - Baltimore, United States Duration: Sep 23 1991 → Sep 25 1991 |
Other
Other | 9th Applied Aerodynamics Conference, 1991 |
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Country/Territory | United States |
City | Baltimore |
Period | 9/23/91 → 9/25/91 |
All Science Journal Classification (ASJC) codes
- Mechanical Engineering
- Aerospace Engineering