Experimental Investigation of Air Film Cooling Applied to an Adiabatic Wall by Means of an Axially Discharging Slot
Low-pressure Performance of Annular, High-pressure (40-atm), High-temperature (2480K) Combustion Systems
Method for Determining Optimum Division of Power Between Jet and Propeller for Maximum Thrust Power of a Turbine-propeller Engine
Effect of Inlet-air Humidity, Temperature, Pressure, and Reference Mach Number on the Formation of Oxides of Nitrogen in a Gas Turbine Combustor
Performance and Emission Characteristics of Swirl-can Combustors to a Near-stoichiometric Fuel-air Ratio
Low-pressure Performance of Annular, High-pressure (40-atm), High-temperature, (2480 K) Combustion System
Effect of flame stabilizer design on performance and exhaust pollutants of a two-row swirl-can combustor operated to near-stoichiometric conditions
Thirty-seventh Annual Report of the National Advisory Committee for Aeronautics. 1951. Including Technical Reports Nos. 1003 to 1058
Effect of Flame Stabilizer Design on Performance and Exhaust Pollutants of a Two-row 72-module Swirl-can Combustor
Experimental Rocket Performance of Apollo Storable Propellants in Engines with Large Area Ratio Nozzles
Analysis of Thrust Augmention of Turbojet Engines by Water Injections at Compressor Inlet Including Charts for Calculating Compression Processes with Water Injection
Analysis of Thrust Augmentation of Turbojet Engines by Water Injection at Compressor Inlet Including Charts for Calculating Compression Processes With Water Injection