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Altitude-Test-Chamber Investigation of a Solar Afterburner on the 24C Engine 1 - Operational Characteristics and Altitude Limits
"An altitude-test-chamber investigation was conducted to determine the operational characteristics and altitude blow-out limits of a Solar afterburner in a 24C engine. At rated engine speed and maximum permissible turbine-discharge temperature, the altitude limit as determined by combustion blow-out occurred as a band of unstable operation of about 8000 feet altitude in width with maximum altitude limits from 32,000 feet at a Mach number of 0.3 to about 42,000 feet at a Mach number of 1.0. The maximum fuel-air ratio of the afterburner, as limited by maximum permissible turbine-discharge gas temperatures at rated engine speed, varied between 0.0295 and 0.0380 over a range of flight Mach numbers from 0.25 to 1.0 and at altitudes of 20,000 and 30,000 feet" (p. 1).
Date:
July 6, 1948
Creator:
Dowman, Harry W. & Reller, John O.
System:
The UNT Digital Library
Charts for Determining Preliminary Values of Span-Load, Shear, Bending-Moment, and Accumulated-Torque Distributions of Swept Wings of Various Taper Ratios
Contains charts for use in determining preliminary values of the spanwise-load, shear, bending-moment, and accumulated-torque distributions of swept wings. The charts are based on strip theory and include four aerodynamic-load distributions, two section-moment distributions, and two inertia-load distributions. The taper ratios considered cover the range from 1.0 to 0 and the results are applicable to any angle of sweep.
Date:
July 6, 1948
Creator:
Wollner, Bertram C.
System:
The UNT Digital Library
Conversations regarding RW
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Date:
July 6, 1948
Creator:
Gast, P. F.
System:
The UNT Digital Library