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Numerical Investigation of Supersonic Transition for a Circular Cone at Mach 3.5

机译：3.5马赫圆锥超音速跃迁的数值研究

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《AIAA Fluid Dynamics Conference and Exhibit》|2008年|P.1-24|共24页
会议地点 Seattle WA(US)
作者
A. Laible; C. Mayer; H. Fasel;
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作者单位

The University of Arizona Tucson AZ;

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1. Numerical Investigation of Wave Packets in a Mach 3.5 Cone Boundary Layer [J] . Christian S. J. Mayer, Andreas C. Laible, Hermann F. Fasel AIAA Journal . 2011,第1期

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2. Numerical Investigation of Transition in a Flared Cone Boundary Layer at Mach 6 [J] . Hermann F. Fasel, Jayahar Sivasubramanian, Andreas Laible Procedia IUTAM . 2015,第2aPartaB期

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3. Numerical Study of Flow Angles and Mach Number Measurement Using the Surface Pressure of a Supersonic Aircraft with Nose Cone [J] . Katsuyoshi Fukiba, Nobuyuki Tsuboi, Hiroaki Kobayashi Transactions of the Japan society for aeronautical and space sciences . 2012,第2期

机译：超音速机鼻锥面流角和马赫数测量的数值研究。
4. Numerical Investigation of Supersonic Transition for a Circular Cone at Mach 3.5 [C] . American Institute of Aeronautics and Astronautics Fluid Dynamics Conference and Exhibit . 2008

机译：马赫3.5圆锥形圆锥形过渡的数值研究
5. Numerical Investigation of Boundary--Layer Transition for Cones at Mach 3.5 and 6.0. [D] . Laible, Andreas C. 2011

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6. Numerical Investigation of Heat Transfer and Friction Factor Characteristics in a Circular Tube Fitted with V-Cut Twisted Tape Inserts [O] . Sami D. Salman, Abdul Amir H. Kadhum, Mohd S. Takriff, 2013

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7. Numerical Investigation of Boundary-Layer Transition for Cones at Mach 3.5 and 6.0 [O] . Laible Andreas Christian 2011

机译：3.5和6.0马赫锥的边界层过渡的数值研究
8. Investigation of Boundry-Layer Transition on 10 deg Cone in Langley 4- by 4-Foot Supersonic Pressure Tunnel at Mach Numbers of 1.41, 1.61, and 2.01 [R] . Sinclair, A. R., Czarnecki, K. R. 1956

机译：Langley 4-4英尺超音速隧道10度锥体边界层转变的研究，马赫数为1.41,1.61和2.01

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