Wind tunnel tests were conducted at subsonic and transonic Mach numbers to determine the performance levels of exhaust nozzles installed in an aircraft. These tests were conducted with dual nozzles mounted in rigs simulating the entire airplane and with a single nozzle installed in a shaft-mounted rig simulating the aft end of half the airplane. Baseline isolated tests were also conducted with a single exhaust nozzle mounted on a cylindrical shaft. These tests showed that the better the simulated installation, the more valid the results. They also showed that a shaft mounted simulated airplane installation could provide valid trends for selecting the optimum nozzle installation.
Performance Installation Effects for Nozzles Installed on a Twin-Jet Fighter Airplane Model
Sae Technical Papers
National Air Transportation Meeting ; 1968
29.04.1968
Aufsatz (Konferenz)
Englisch
Performance installation effects for nozzles installed on twin-jet fighter airplane model
Engineering Index Backfile | 1968
|Comparison of Non-Axisymmetric & Axisymmetric Nozzles Installed on a V/STOL Fighter Model
SAE Technical Papers | 1977
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