Aerodynamic Heating in the Gap Between a Missile Body and a Control Fin-Reference-Cited by-同舟云学术

Aerodynamic Heating in the Gap Between a Missile Body and a Control Fin

Published:2022-07 Issue:4 Volume:59 Page:1111-1124
ISSN:0022-4650
Container-title:Journal of Spacecraft and Rockets
language:en
Short-container-title:Journal of Spacecraft and Rockets

Author:

Alviani Robert¹,Fano Devon¹,Poggie Jonathan¹,Blaisdell Gregory¹

Affiliation:

1. Purdue University, West Lafayette, Indiana 47907

Funder

Air Force Research Laboratory

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Space and Planetary Science,Aerospace Engineering

Link

https://arc.aiaa.org/doi/pdf/10.2514/1.A35183

Reference15 articles.

1. GudmundssonS., General Aviation Aircraft Design Applied Methods and Procedures, 1st ed. Butterworth-Heinemann, Oxford, England, U.K., 2014, pp. 714–740.

2. DéleryJ.MarvinJ. G.ReshotkoE. “Shock-Wave Boundary Layer Interactions,” Advisory Group for Aerospace Research and Development TR 280, Neuilly-Sur-Seine, France, 1986.

3. Progress in shock wave/boundary layer interactions

4. TauberM. E. “A Review of High-Speed, Convective, Heat-Transfer Computation Methods,” NASA Office of Management TR 2914, 1989.

5. Effect of gap size on pressure and heating over the flap of a blunt delta wing in hypersonic flow.

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