1 Van Dyke, M., "The supersonic blunt-body problem—review and extensions/' J. Aeronaut. Sci. 25, 485-496 (1958). 2 Garabedian, P. R. and Lieberstein, H. M., "On the numerical calculation of detached bow shock waves in hypersonic flow," J. Aeronaut. Sci. 25, 109-118 (1958). 3 Swigart, R., "Hypersonic blunt-body flowfields at angle of attack," AIAA J. 2, 115-117 (1964). 4 Swenson, E. V., "Numerical computation of hypersonic flow past a two-dimensional blunt body," Atomic Energy Commission Research and Development Rept. NYO 1480-1, Courant Institute of Mathematical Sciences, New York Univ. (1964). 5 Bielotserkovskii, O. M., "On the calculation of flow past axisymmetric bodies with detached shock waves using an electronic computing machine," Prikl. Mat. Mekh. 24, 511-517 (1960). 6 Prosnak, W. J. and Luczywek, E., "The direct asymmetric hypersonic blunt-body problem," AIAA Preprint 64-552 (1964). 7 Bazzhin, A. P., "On the computation of the supersonic flow about a flat plate with a detached shock wave," Inzh. Zh. 3, 222227 (1963). 8 Waldman, G. D., "Integral approach to the yawed blunt body problem," AIAA Paper 65-28 (1965). 9 Godunov, S. K., Zabrodin, A. O., and Prokopov, G. P., "A difference scheme for two-dimensional unsteady flow with a detached shock wave," Zh. Vychyslitelnoi Mat. Mat, Fiz. I, 10201050 (1961); also available as a Cornell Aeronautical Lab. transl. 10 Bohachevsky, I. O. and Rubin, E. L., "A direct method for computation of nonequilibrium flows with detached shock waves," AIAA J. 4, 600-607 (1966). 11 Lax, P. D., "Weak solutions of nonlinear hyperbolic equations and their numerical computations," Commun. Pure Appl. Math. 7, 159-193 (1954). 12 Kaattari, G. E., "Shock envelopes of blunt bodies at large angles of attack," NASA TN D-1980 (December 1963). 13 Vaglio-Laurin, R., "Transonic rotational flow over a convex corner," J. Fluid Mech. 9, 81-103 (1960). 14 Kaattari, G. E., "Predicted shock envelopes about two types of vehicles at large angles of attack," NASA TN D-860 (April 1961).
[1]
Harold Mirels,et al.
TEST TIME IN LOW PRESSURE SHOCK TUBES
,
1963
.
[2]
H. Mirels.
Laminar Boundary Layer Behind a Strong Shock Moving into Air
,
1961
.
[3]
Ronald F. Probstein,et al.
THE TRANSVERSE CURVATURE EFFECT IN COMPRESSIBLE AXIALLY-SYMMETRIC LAMINAR BOUNDARY LAYER FLOW
,
1956
.
[4]
Russell E. Duff,et al.
Shock‐Tube Performance at Low Initial Pressure
,
1959
.
[5]
H. Mirels.
Shock Tube Test Time Limitation Due to Turbulent-Wall Boundary Layer
,
1964
.
[6]
Harold Mirels,et al.
Boundary layer behind shock or thin expansion wave moving into stationary fluid
,
1956
.
[7]
A. Roshko.
On Flow Duration in Low‐Pressure Shock Tubes
,
1960
.
[8]
Measurements of test time in the galcit 17-inch shock tube
,
1964
.
[9]
Harold Mirels,et al.
Laminar boundary layer behind shock advancing into stationary fluid
,
1955
.