The present paper investigates the critical heating phenomena at the winglet reentry vehicles. The study is restricted to flow situation without bow shock winglet interactions. It is found that attachment line heating on the leading edge of the winglet and on the lower edge of the rudder can be predicted with a Navier-Stokes code. The simulations reveal a strong sensitivity of winglet heating with respect to the angle of attack. The validity of engineering models to predict heating rates during preliminary design cycles is also investigated. It is found that the swept cylinder analogy cannot simulate the sensitivities observed. High-temperature effects on attachment line heating are assessed by comparing the solutions for cold wind tunnel flow conditions with solutions on a reentry trajectory point assuming air in thermomechanical equilibrium. It is found that the peak heating rates on the wing compare reasonably well provided they are scaled as Stanton-Miller numbers.
Critical flow phenomena on the winglet of winged reentry vehicles
Kritische Strömungsphänomene am Tragflächenansatz von Tragflächenraumfahrzeugen
Zeitschrift für Flugwissenschaften und Weltraumforschung ; 19 , 5 ; 309-319
1995
11 Seiten, 19 Bilder, 1 Tabelle, 15 Quellen
Aufsatz (Zeitschrift)
Englisch
Critical flow phenomena on the winglet of winged reentry vehicles
Online Contents | 1995
|Critical Flow Phenomena on the Winglet of Winged Reentry Vehicles
British Library Conference Proceedings | 1994
|Critical Flow Phenomena on the Winglet of Winged Reentry Vehicles
British Library Conference Proceedings | 1994
|Attachment heating on the winglet of winged reentry vehicles
British Library Conference Proceedings | 1995
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