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  Partner: UNT Libraries Government Documents Department
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselage-store Configurations. Ii - Swept-wing Heavy-bomber Configuration With Large Store Nacelle . Lateral Forces and Pitching Moments, Mach Number, 1.61

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselage-store Configurations. Ii - Swept-wing Heavy-bomber Configuration With Large Store Nacelle . Lateral Forces and Pitching Moments, Mach Number, 1.61

Date: July 6, 1955
Creator: Carlson, H. W.
Description: Effect of large store /nacelle/ on a swept-wing heavy bomber - lateral force and pitching moments.
Contributing Partner: UNT Libraries Government Documents Department
The origin and distribution of supersonic store interference from measurement of individual forces on several wing-fuselage-store configurations III : swept-wing fighter-bomber configuration with large and small stores. Mach number 1.61

The origin and distribution of supersonic store interference from measurement of individual forces on several wing-fuselage-store configurations III : swept-wing fighter-bomber configuration with large and small stores. Mach number 1.61

Date: September 15, 1955
Creator: Smith, Norman F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The origin and distribution of supersonic store interference from measurement of individual forces on several wing-fuselage-store configurations V : swept-wing heavy-bomber configuration with large store (nacelle).  Mach number 2.01

The origin and distribution of supersonic store interference from measurement of individual forces on several wing-fuselage-store configurations V : swept-wing heavy-bomber configuration with large store (nacelle). Mach number 2.01

Date: February 13, 1956
Creator: Carson, Harry W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. 1.-swept-wing Heavy-bomber Configuration With Large Store Nacelle . Lift and Drag, Mach Number, 1.61

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. 1.-swept-wing Heavy-bomber Configuration With Large Store Nacelle . Lift and Drag, Mach Number, 1.61

Date: March 11, 1955
Creator: Carlson, H. W.
Description: Supersonic store interference - 1, swept-wing heavy bomber with large stores - lift & drag at mach 1.61.
Contributing Partner: UNT Libraries Government Documents Department
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. Iii - Swept-wing Fighter-bomber Configuration With Large and Small Stores. Mach Number, 1.61

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. Iii - Swept-wing Fighter-bomber Configuration With Large and Small Stores. Mach Number, 1.61

Date: September 15, 1955
Creator: Carlson, H. W.
Description: Origin of supersonic store interference from measurements of individual forces - swept-wing fighter-bomber with large & small stores.
Contributing Partner: UNT Libraries Government Documents Department
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. Vi - Swept-wing Heavy-bomber Configuration With Stores of Different Sizes and Shapes

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. Vi - Swept-wing Heavy-bomber Configuration With Stores of Different Sizes and Shapes

Date: March 8, 1956
Creator: Smith, N. F.
Description: Effect of stores on a swept-wing heavy bomber.
Contributing Partner: UNT Libraries Government Documents Department
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wingfuselage-store Configurations. Iv.-delta-wing Heavy-bomber Configuration With Large Store. Mach Number, 1.61

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wingfuselage-store Configurations. Iv.-delta-wing Heavy-bomber Configuration With Large Store. Mach Number, 1.61

Date: December 15, 1955
Creator: Morris, O. A.
Description: Origin and distribution of supersonic store interference/measurement of individual forces on delta-wing heavy bomber configuration mach 1.61.
Contributing Partner: UNT Libraries Government Documents Department
The Origin and Distribution of Supsonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. V - Swept-wing Heavy-bomber Configuration With Large Store Nacelle . Mach Number 2.01

The Origin and Distribution of Supsonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. V - Swept-wing Heavy-bomber Configuration With Large Store Nacelle . Mach Number 2.01

Date: February 13, 1956
Creator: Carlson, H. W.
Description: Origin & distribution of supersonic store interference/measurement of individual forces - swept-wing heavy bomber with large store figure.
Contributing Partner: UNT Libraries Government Documents Department
Origin and prevention of crash fires in turbojet aircraft

Origin and prevention of crash fires in turbojet aircraft

Date: May 1, 1957
Creator: Pinkel, I Irving
Description: The manner in which the jet engine may start a crash fire was explored in test-stand and full-scale crash studies. On the basis of these studies, a method was devised for inserting and cooling the engine parts that may serve as ignition sources in crash. This method was tried successfully in full-scale crashes of jet-powered airplanes carrying engines in pod nacelles and engines buried within the airplane structure.
Contributing Partner: UNT Libraries Government Documents Department
Origin and Prevention of Crash Fires in Turbojet Aircraft

Origin and Prevention of Crash Fires in Turbojet Aircraft

Date: January 1, 1958
Creator: Pinkel, I. Irvin
Description: The tendency for the jet engine rotor to continue to rotate after crash presents the probability that crash-spilled combustibles suspended in the air or puddled on the ground at the engine inlet may be sucked into the engine. Studies with jet engines operating on a test stand and full-scale crashes of turbojet-powered airplanes showed that combustibles drawn into the engine in this way ignite explosively within the engine. Experiment showed that the gas flow through the engine is too rapid to permit the ignition of ingested combustibles on the hot metal in contact with the main gas stream. Ignition will occur on those hot surfaces not in the main gas stream. The portion of the engine airflow is diverted for cooling and ventilation to these zones where the gas moves slowly enough for ignition to occur.
Contributing Partner: UNT Libraries Government Documents Department