H. Ikawa

Ignition/duct overpressure induced by Space Shuttle solid rocket motor ignition

H. Ikawa, F. S. Laspesa, H. Ikawa, 1985 .

A reentry hypersonic control effectiveness methodology as applied tothe Space Shuttle Orbiter

H. Ikawa, 1977 .

Real gas laminar boundary layer separation methodology as applied to Orbiter control surface effectiveness prediction

H. Ikawa, 1979 .