Early supersonic combustion studies at NACA and NASA

Pinkel, 1950, Graphical Method for Obtaining Flow Field in Two Dimensional Supersonic Stream to Which Heat is Added, NACA TN, 2206 Pinkel, 1952, Pressure Distribution and Aerodynamic Coefficients Associated with Heat Addition to Supersonic Air Stream Adjacent to Two-Dimensional Supersonic Wing, NACA RM E51K26 Straight, 1953, Aluminum Borodydride as an Ignition Source for Turbojet Combustors, NACA RM E55G15 Foster, 1955, Aluminum Borohydride Hydrocarbon Mixtures as a Source of Ignition for a Turbojet Combustor, NACA RM E54K12 Fletcher, 1955, Combustion of Aluminum Borohydride in a Supersonic Wind Tunnel, NACA RM E55D07a Dorsch, 1955, A Preliminary Investigation of Static-Pressure Changes Associated with Combustion of Aluminum Borohydride in a Supersonic Wind Tunnel, NACA RM E55F07 Allen, 1959, Combustion of Various Highly Reactive Fuel in a 3.84- by 10-inch Mach 2 Wind Tunnel, NASA Memo 1-15-59E Allen, 1960, A Study of the Combustion of Aluminum Borohydride in a Small Supersonic Wind Tunnel, NASA TN D-296 Dorsch, 1957, Exploratory Investigation of Aerodynamic Effects of External Combustion of Aluminum Borohydride in Airstream Adjacent to Flat Plate in Mach 2.46 Tunnel, NACA RM E57E16 Serafini, 1957, Exploratory Investigation of Static and Base-Pressure Increases Resulting from Combustion of Aluminum Borohydride Adjacent to Body of Revolution in Supersonic Wind Tunnel, NACA RM E57E15 Dorsch, 1959, Experimental Investigation of Aerodynamic Effects of External Combustion in Airstream Below Two-Dimensional Supersonic Wing at Mach 2.5 and 3.0, NASA Memo 1-11-59E Dorsch, 1960, Investigation of Aerodynamic Effects of External Combustion below Flat-Plate Model in 10- by 10-foot Wind Tunnel at Mach 2.4, NASA TN D-282