The calculation of transition on an infinite swept wing has been investigated for a range of sweep angles. Reynolds numbers and angles of attack. The method solves boundary-layer and Orr-Sommerfeld equations by a finite-difference procedure and involves interaction with the inviscid flow. Amplification rates in the en-method are determined with an eigenvalue procedure which determines the relationship between the wave numbers. The calculation method is evaluated in terms of measurements reported for the flow around an ONERA-D wing equipped with a cambered leading edge and attached to a half fuselage. It is shown to be convenient to use, particularly because the neutral stability curves (zarfs) facilitate the calculation and avoid uncertainties associated with the choice of magnitude and location of the critical frequencies. In general, the calculated values of the onset of transition are in good agreement with measured values, for the eight cases examined.
A three-dimensional linear stability approach to transition on wings at incidence
Eine dreidimensionale lineare Stabilitaetsmethode fuer den Uebergang auf Fluegeln am Eintritt
1989
13 Seiten, 17 Bilder, 1 Tabelle, 20 Quellen
Aufsatz (Konferenz)
Englisch
Stability and transition on swept wings
AIAA | 1993
|Rapid Scheme for Estimating Transition on Wings by Linear Stability Theory
British Library Online Contents | 1994
|Rapid Scheme for Estimating Transition on Wings by Linear Stability Theory
British Library Conference Proceedings | 1994
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