National Advisory Committee for Aeronautics (NACA) - 8 Matching Results

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A comparison of the simulated-altitude performance of two turbojet combustor types

Description: Report presenting a comparison of the performance of a German Jumo 004 can-type combustor and the performance of two contemporary United States turbojet combustors to determine whether the Jumo 004 was more advanced and to determine whether there are basic, inherent differences in the performance achieved with the can or annular combustor type. Results regarding altitude operational limits, combustion efficiency, pressure loss, and temperature profile at combustor outlet are provided.
Date: October 7, 1948
Creator: Bolz, Ray E.; Schroeter, Thomas T. & Zettle, Eugene V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of the effects of support interference on the drag of bodies of revolution at a Mach number of 1.5

Description: Testing was conducting to evaluate the effects of support interference on the drag characteristics of two bodies of revolution at zero angle of attack at Mach number 1.5. Drag and base-pressure measurements are made for a variety of Reynolds numbers to determine the effect of varying the length or diameter of the rear support.
Date: May 7, 1948
Creator: Perkins, Edward W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of conical jet nozzles in terms of flow and velocity coefficients

Description: Performance characteristics of conical jet nozzles were determined in an investigation covering a range of pressure ratios from 1.0 to 2.8, cone half-angles from 5 degrees to 90 degrees, and outlet-inlet diameter ratios from 0.50 to 0.91. All nozzles investigated had an inlet diameter of 5 inches. The flow coefficients of the conical nozzles investigated were dependent on the cone half-angle, outlet-inlet diameter ratio, and pressure ratio. The velocity coefficients were essentially constant at… more
Date: September 7, 1948
Creator: Grey, Ralph E. & Wilsted, H. Dean
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Drag Characteristics of a Wing-Body Combination Showing the Effect of a Large Wing Fillet

Description: "Results of an investigation by the free-fall method are presented herein for a configuration having a body of revolution of fineness ratio 12 and 45 degrees sweptback wing mounted aft of the maximum diameter of the body. The fillets were designed to provide large increases in the sweep of the leading edge and the line of maximum thickness as the wing root was approached. Comparison of these results with those for the same configuration without fillets shows that the addition of wing fillets in… more
Date: September 7, 1948
Creator: Cheatham, Donald C. & Kurbjun, Max C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical analysis of the motions of an aircraft stabilized in roll by a displacement-response, flicker-type automatic pilot

Description: Report presenting a general analysis that allows the rolling motions of an aircraft using a displacement-response, flicker-type automatic pilot to be determined. The system is not ideal for many stabilization problems due to inherent residual oscillations, but it offers a simple and economical solution in situations in which steady state oscillations are not a problem. Results regarding some general remarks, transient and steady states, stabilization boundaries, amplitude equations, and period … more
Date: July 7, 1948
Creator: Curfman, Howard J., Jr. & Gardner, William N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of combustion in flowing gas with various turbulence promoters

Description: Report presenting an investigation of combustion occurring downstream of various turbulence promoters in a 20-inch length of a 1 7/8-inch inside-diameter, water-jacketed tubing using premixed vaporized fuel and air. Among the turbulence promoters investigated were flat plates perforated with 1/8-inch diameter holes, 1/4-inch diameter holes, and a single large hole to give 12.4, 17.2, and 21.5 percent open area respectively.
Date: June 7, 1948
Creator: Haddock, Gordon W. & Childs, J. Howard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of Various Ailerons on a 42 Degree Sweptback Wing for Lateral Control at Transonic Speeds

Description: Report presenting an investigation at transonic speeds in the high speed tunnel to determine the rolling-effectiveness characteristics of several aileron arrangements for use on a 42 degree sweptback wing. Results regarding the rolling-moment coefficients, variation of coefficient with Mach number, outboard cusp aileron, and use of the leading-edge flaps are provided.
Date: September 7, 1948
Creator: Turner, Thomas R.; Lockwood, Vernard E. & Vogler, Raymond D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ditching tests of a 1/15-scale model of the Fairchild C-82 airplane

Description: Given here are results of tests made in calm water at various landing attitudes, speeds, and simulated conditions of damage. It was concluded that the best ditching could be made by contacting the water as near the stall angle as possible without losing adequate control. The landing flaps should be full down. If the paratainer hatch and aft-cargo doors fail as expected in a ditching, there will be a large inrush of water into the cargo compartment which makes this location a very hazardous ditc… more
Date: October 7, 1948
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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