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Effect of Inlet Temperature on Rotating Stall and Blade Vibrations in a Multistage Axial-Flow Compressor
Report presenting rotating-stall and blade-vibration data for the first three rotor blade rows of a 13-stage axial-flow compressor at several inlet temperatures. Stall patterns of 1 through 5 stall zones were detected at all inlet temperatures in the equivalent compressor speed ranges between 4600 and 6200 rpm.
Date:
August 5, 1955
Creator:
Medeiros, Arthur A.; Calvert, Howard F. & Fenn, David B.
System:
The UNT Digital Library
Flight Measurements of the Lateral Response Characteristics of the Convair XF-92A Delta-Wing Airplane
Memorandum presenting rudder pulse maneuvers obtained with the Convair XF-92A delta-wing research airplane at an altitude of about 30,000 feet over a Mach number range of 0.52 to 0.92. Tests were made with and without a wing fence. By analyzing the maneuvers, the characteristics of the airplane transient, airplane stability derivatives, and frequency-response characteristics were measured.
Date:
August 5, 1955
Creator:
Holleman, Euclid C.
System:
The UNT Digital Library
Stall and flame-out resulting from firing of armament
Report presenting an analysis of the causes of compressor stall and flame-out when armament is fired during flight at high altitudes. Experimental data are also presented. The increase in compressor-inlet temperature during armament firing was found to be the most important single factor affecting engine performance.
Date:
August 5, 1955
Creator:
Childs, J. Howard; Kochendorfer, Fred D.; Lubick, Robert J. & Friedman, Robert
System:
The UNT Digital Library