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Carbon deposition from AN-F-58 fuels in a J33 single combustor

Description: Report presenting an investigation using a single combustor from a 4600-pound-thrust turbojet engine to determine the amount of carbon deposition of AN-F-58 fuels and the effect of carbon formations in the combustor on the altitude operational limits. Three fuel blends conforming to AN-F-58 specification were prepared in order to determine the influence of boiling temperature and of aromatic content on carbon deposition. Results regarding carbon deposition and effect of carbon formations on alt… more
Date: June 24, 1949
Creator: Wear, Jerrold D. & Douglass, Howard W.
Item Type: Refine your search to only Report
open access

Free-Spinning-Tunnel Investigation of a 1/20-Scale Model of the McDonnell XF2H-1 Airplane

Description: A spin-recovery investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 20-scale model modified to represent the McDonnell XF2H-1 airplane. The project included tests both with tip tanks installed and with the tanks removed. The results indicated that the recovery characteristics of the airplane would be satisfactory for all loadings by normal recovery technique (full reversal of the rudder, followed 1/2 turn later by movement of the elevator down). The rudder pedal an… more
Date: June 24, 1949
Creator: Berman, Theodore
Item Type: Refine your search to only Report
open access

Graphite contaminant tests for DR&H piles (C-206A, HW24, C-165A, HW24)

Description: This report outlines plans for tests of the graphite stack during lay up in the pile structures. Measurements are planned upon completion of layers 20, 60, and 102, which will require not more than 16 hours each. The test method will require restriction of Construction personnel from the areas immediately adjacent to the pile. Precise boundaries will be set up in collaboration with H I Division personnel prior to the test.
Date: June 24, 1948
Creator: Burns, J. A.
Item Type: Refine your search to only Report
open access

An Investigation of the Lateral-Control Characteristics of Spoilers on a High-Aspect-Ratio Wing of NACA 65-210 Section in the Langley 8-Foot High Speed Tunnel

Description: Report presenting a lateral-control investigation of 3- and 6-percent chord spoilers projecting on the upper surface of a wing of high-aspect ratio. The spoilers were found to give large rolling moments at Mach numbers below the Mach number corresponding to the break in the rolling-moment-coefficient curves. Results regarding section pressure distributions, rolling-moment characteristics, normal-force characteristics, pitching-moment characteristics, wing-torsional considerations, and hinge-mom… more
Date: June 24, 1947
Creator: Luoma, Arvo A.
Item Type: Refine your search to only Report
open access

Limited measurements of static longitudinal stability in flight of Douglas D-558-1 airplane (BuAero No. 37971)

Description: Contains a few measurements of the variation of elevator angle and elevator force with Mach number at 30,000 feet altitude up to a Mach number of 0.85. These data show that the airplane possessed positive static longitudinal stability up to a Mach number of 0.80. A trim change in the nose-down direction occurred for Mach numbers above 0.82.
Date: June 24, 1948
Creator: Williams, Walter C.
Item Type: Refine your search to only Report
open access

A Thermal Type Flow Meter for Low Flow Rates of Anhydrous Hydrofluoric Acid

Description: Report discussing a thermal type flow meter which was adapted for metering anydrous hydrofluoric acid at low flow rates. Corrosive gases, which are not appropriate for handling in standard type rotameters or orifice meters, are also suitable for this thermal type flow meter.
Date: June 24, 1946
Creator: Johnsson, Karl Otto; Peed, W. F. & Clewett, G. H.
Item Type: Refine your search to only Report
open access

Wind-tunnel investigation of a tailless triangular-wing fighter aircraft at Mach numbers from 0.5 to 1.5

Description: Report presenting a wind-tunnel investigation to determine the respective variations with Mach number of the static longitudinal stability, the drag, and the effectiveness of a constant-chord control surface for a tailless fighter aircraft with a triangular wing of aspect ratio 2.31.
Date: June 24, 1949
Creator: Lawrence, Leslie F. & Summers, James L.
Item Type: Refine your search to only Report
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