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The Design of Variable Mach Number Asymmetric Super-Sonic Nozzles by Two Procedures Employing Inclined and Curved Sonic Lines
"Two theoretical procedures are developed for designing asymmetric supersonic nozzles for which the calculated exit flow is nearly uniform over a range of Mach numbers. One procedure is applicable at Mach numbers less than approximately 3. This approach yields, without iteration, a nozzle for which the calculated exit flow is uniform at two Mach numbers and, with proper design, is nearly uniform at Mach numbers between, slightly above, and slightly below these two" (p. 1).
Date:
April 11, 1951
Creator:
Syvertson, Clarence A. & Savin, Raymond C.
System:
The UNT Digital Library
Flight Investigation of the Effect of Sideslip on the Pressure at the Static Orifices of the Boeing B-29 Airplane
Report discussing testing to determine the sensitivity to sideslip of the static-pressure orifices of the Boeing B-29. The purpose was to determine the errors in indicated altitude and vertical velocity that occur when an airplane experiences oscillations in sideslip on a bombing run. The sensitivity of the orifices to sideslip was determined by measurements of pressure and sideslip angle during constant-amplitude oscillations in sideslip.
Date:
April 11, 1951
Creator:
Chilton, Robert G. & Brown, B. Porter
System:
The UNT Digital Library