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Combustion properties of aluminum as ram-jet fuel

Description: Report presenting an experimental investigation to determine the combustion properties of aluminum as a fuel for use in high-speed aircraft. The aluminum fuel was injected both in powder and wire form into 2-inch-diameter ramjet-type combustors. Results regarding operational problems, thrust, and combustion efficiency are provided.
Date: March 28, 1951
Creator: Branstetter, J. Robert; Lord, Albert M. & Gerstein, Melvin
Item Type: Refine your search to only Report
open access

Comparison of High-Speed Operating Characteristics of Size 215 Cylindrical-Roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig

Description: "A comparison of the operating characteristics of 75-millimeter-bore (size 215) cylindrical-roller one-piece inner-race-riding cage-type bearings was made using a laboratory test rig and a turbojet engine. Cooling correlation parameters were determined by means of dimensional analysis, and the generalized results for both the inner- and outer-race bearing operating temperatures are compared for the laboratory test rig and the turbojet engine. Inner- and outer-race cooling-correlation curves wer… more
Date: November 28, 1951
Creator: Macks, E. Fred & Nemeth, Zolton N.
Item Type: Refine your search to only Report
open access

Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers From 1.59 to 1.99 4: Conical-Spike External-Internal Compression Inlet Utilizing Perforated Cowl

Description: Report presenting testing conducted to determine the force and pressure-recovery characteristics of a model utilizing a single-shock spike-type inlet with a perforated cowl. The use of the cowl resulted in the attainment of a high pressure recovery at zero angle of attack, but it was accompanied by a relatively large increase in external drag as compared with nonperforated inlets of the same proportions. Results regarding the characteristics at zero angle of attack, effects of changes in angle … more
Date: March 28, 1951
Creator: Madden, Robert T. & Kremzier, Emil J.
Item Type: Refine your search to only Report
open access

An Investigation of the Drag and Pressure Recovery of a Submerged Inlet and a Nose Inlet in the Transonic Flight Range With Free-Fall Models

Description: "The drag and pressure recovery of an NACA submerged-inlet model and an NACA series I nose-inlet model were investigated in the transonic flight range. The tests were conducted over a mass-flow-ratio range of 0.4 to 0.8 and a Mach number range of about 0.8 to 1.10 employing large-scale recoverable free-fall models. The results indicate that the Mach number of drag divergence of the inlet models was about the same as that of a basic model without inlets" (p. 1).
Date: December 28, 1951
Creator: Selna, James & Schlaff, Bernard A.
Item Type: Refine your search to only Report
open access

An investigation of the spray characteristics of a jet-powered dynamic model of the drag flying boat with a vee tail : TED No. NACA DE 328

Description: An investigation was made of the spray characteristics of a jet-powered dynamic model of the Bureau of Aeronautics DR 56 flying-boat design with a vee tail. A limited investigation was made to determine the effect of the change in tail design on the take-off and landing behavior in smooth water and in waves 8 feet high (full size).
Date: February 28, 1951
Creator: Carter, Arthur W.
Item Type: Refine your search to only Report
open access

Performance of a Cascade in an Annular Vortex-Generating Tunnel Over Range of Reynolds Numbers

Description: Total-pressure deficiency for an annular cascade of 65-(12)10 blades was measured at three radial stations over a range of Reynolds numbers from 50,000 to 250,000 and at angles of attack of 15 degrees and 25 degrees. The variation of turning angle and shape of static pressure distribution at these stations is also shown.
Date: September 28, 1951
Creator: Thurston, Sidney & Brunk, Ralph E.
Item Type: Refine your search to only Report
open access

Preliminary investigation of a translating cowl technique for improving take-off performance of a sharp-lip supersonic diffuser

Description: A preliminary investigation was conducted in quiescent air on a translating cowl technique for improving the take-off performance of a sharp-lip supersonic diffuser. The technique consists of cutting the cowling in a plane normal to its axis and then translating the forepart of the cowling in the forward direction. The leading edge of the fixed portion of the cowling is rounded. Appreciable improved inlet performance was obtained with a cowling translation corresponding to a gap of only 1/4 inl… more
Date: November 28, 1951
Creator: Cortright, Edgar M., Jr.
Item Type: Refine your search to only Report
open access

Some low-speed characteristics of an air-induction system having scoop-type inlets with provisions for boundary-layer control

Description: Report presenting an investigation conducted at low speed of an air-induction system with twin scoop-type inlets on the sides of the fuselage of a model of an airplane designed for flight at supersonic Mach numbers. The leading edge of the lip of the scoop was rounded and there were provisions for control of the boundary layer ahead of the inlet. Results regarding the characteristics of the lips investigated, characteristics of the main duct with lip E, characteristics of the boundary layer con… more
Date: August 28, 1951
Creator: Watson, Earl C.
Item Type: Refine your search to only Report
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