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Resonance Absorption in Lumps and Mixtures

Description: The resonance absorption of a lump is described in terms of three components. Calculations of resonance absorption are carried out using the model for the resonance spectrum of uranium recently derived; calculations are also made with variations of this model which involve local fluctuations in level strengths. For metal and oxide lumps the agreement with observation is satisfactory. For dilute mixtures, whose resonance activation was measured by Mitchell, computed values fall 20% to 30% above … more
Date: April 17, 1944
Creator: Dancoff, Sidney M., 1913-1951 & Gingburg, M.
Item Type: Refine your search to only Report
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Warping Instability in Long Rods

Description: Abstract. If a pile rod gets bowed within its cooling tube it becomes warmer on the side which approaches the tube wall, and thermal expansion tends to warp it in the same direction as the original displacement. This was discussed roughly in N-601, and it was there concluded that the mechanism was not important for an isolated short slug. In connection with current development of continuous jacket (cartridge) assemblies, it seems desirable to look at this question again. In this case it is poss… more
Date: August 17, 1944
Creator: Young, Gale Jay
Item Type: Refine your search to only Report
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Charts of Compressibility Factors and Charts Showing Quantities Delivered by Commercial Cylinders for Hydrogen, Nitrogen, and Oxygen

Description: Two charts are given for each of the gases hydrogen, nitrogen, and oxygen. The first gives directly the number of standard cubic feet of the gas which a cylinder will deliver. The second chart gives values of the compressibility factor and of the density.
Date: November 17, 1948
Creator: Hoge, Harold J.; Meyers, Cyril H. & McCoskey, Robert E.
Item Type: Refine your search to only Report
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Separation of Iron and Tuballoy With Phthallic Acid

Description: Introduction: This report embodies the results of an investigation as to the possibility of removing the bulk of the iron from gunk solutions of various concentrations by precipitation of the iron with phthallic acid and subsequent precipitation of tuballoy. The method consists of dissolving the phthallic acid in the gunk solution and then adding NH₃ to a suitable pH, precipitating the iron, and leaving the tuballoy in solution.
Date: January 17, 1945
Creator: Hoffman, R. E.; Armstrong, G. M.; Miller, A. J. & Gates, J. W., Jr.
Item Type: Refine your search to only Report
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Recovery of Uranium From Contaminated Precipitron Oil

Description: Abstract: The distillation and residue extraction recovery procedures developed for the recovery of uranium from Kinney and diffusion pump oil, were applied to contaminated precipitron oil. The effectiveness and advisability of using the method, in whole or in part, is discussed, and various recommendations for processing this particular type of oil are presented. Additional contaminating substances present in this type of oil added to the complexity of the problem but a satisfactory recovery p… more
Date: April 17, 1947
Creator: Lee, J. E.; Aikin, L. M. & Susano, C. D.
Item Type: Refine your search to only Report
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A Method for Predicting the Stability in Roll of Automatically Controlled Aircraft Based on the Experimental Determination of the Characteristics of an Automatic Pilot

Description: Report presenting a method for predicting the stability of automatically controlled aircraft by comparing the calculated frequency-response curves for the aircraft and experimentally determined frequency-response curves for the automatic pilot. The method is applicable only to stabilization in roll. It can be used to establish the specifications of performance required for the automatic control device for pilotless aircraft designed as missiles.
Date: January 17, 1947
Creator: Jones, Robert T. & Sternfield, Leonard
Item Type: Refine your search to only Report
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Investigation of shock diffusers at Mach number 1.85 2: projecting double-shock cones

Description: Report presenting an investigation in the 18- by 18-inch supersonic tunnel to determine the total-pressure recovery obtainable at Mach number 1.85 with a shock diffuser with projective cones designed to produce two oblique shocks ahead of the diffuser inlet. The variation of total-pressure recovery with tip projection was investigated for four cones with different included angles. A maximum total-pressure recovery of 94.5 percent was attained with the best configuration at an angle of 0 degrees. more
Date: June 17, 1947
Creator: Moeckel, W. E.; Connors, J. F. & Schroeder, A. H.
Item Type: Refine your search to only Report
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Longitudinal Stability and Control Characteristics of an Airplane Model Having a 42.8 Degree Sweptback Circular-Arc Wing With Aspect Ratio 4.00, Taper Ratio 0.50, and Sweptback Tail Surfaces

Description: Report presenting testing of an airplane model with a 42.8 degree sweptback wing with an aspect ratio of 4.00, taper ratio of 0.50, and a 42.8 degree sweptback horizontal tail, and a 40.3 degree sweptback vertical tail to determine its low-speed longitudinal stability and control characteristics. Other variables investigated include the vertical-wing location, fuselage size, horizontal-tail location, and stall-control vanes on the wing.
Date: October 17, 1947
Creator: Weil, Joseph; Comisarow, Paul & Goodson, Kenneth W.
Item Type: Refine your search to only Report
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Lateral stability and control characteristics of an airplane model having 42.8 degree sweptback circular-arc wing with aspect ratio 4.00, taper ratio 0.50, and sweptback tail surfaces

Description: Report presenting testing in the 300 mph 7- by 10-foot tunnel of an airplane model with a 42.8 degree sweptback wing with an aspect ratio 4.00, taper ratio 0.50, a 42.8 degree sweptback horizontal tail, and a 40.3 degree sweptback vertical tail to determine the low-speed lateral stability and control characteristics. Some changes made to improve the aerodynamic characteristics included lowering the wing, incorporating a smaller-fineness-ratio fuselage, and increasing the vertical tail size. Res… more
Date: October 17, 1947
Creator: Goodson, Kenneth W. & Comisarow, Paul
Item Type: Refine your search to only Report
open access

Performance of 24-Inch Supersonic Axial-Flow Compressor in Air 1: Performance of Compressor Rotor at Design Tip Speed of 1600 Feet Per Second

Description: Memorandum presenting an investigation of an axial-flow compressor rotor operating with supersonic velocities relative to the blade rows in order to determine the performance characteristics in air and to confirm the performance obtained in Freon-12 at another laboratory. Results regarding the weight flow, work of compression, pressure ratio and adiabatic efficiency, and entry of shock are provided.
Date: May 17, 1948
Creator: Ritter, William K. & Johnsen, Irving A.
Item Type: Refine your search to only Report
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Wind-tunnel investigation of horizontal tails 3: unswept and 35 degrees swept-back plan forms of aspect ratio 6

Description: Report presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of two semispan horizontal tails with unswept and 35 degree sweptback plan forms. Test results are provided for models with and without standard roughness on their leading edges and with sealed and unsealed radius-nose elevators. Results regarding effectiveness and hinge-moment parameters, static longitudinal stability, effect of standard roughness, and effect of removing the elevator nose … more
Date: December 17, 1948
Creator: Dods, Jules B., Jr.
Item Type: Refine your search to only Report
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A theoretical lateral-stability analysis of XC-120 airplane

Description: "A theoretical lateral-stability analysis of the XC-120 airplane, equipped with a detachable fuselage, was made to determine the effect on the lateral stability of the high angle of wing incidence for which the airplane was designed. The results of the investigation indicated that the lateral stability of the airplane is satisfactory with or without the detachable fuselage installed" (p. 1).
Date: September 17, 1948
Creator: Sternfield, Leonard & Gates, Ordway B., Jr.
Item Type: Refine your search to only Report
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Preliminary Wind-Tunnel Tests of Triangular and Rectangular Wings in Steady Roll at Mach Numbers of 1.62 and 1.92

Description: Report presenting the damping-in-roll coefficients for a series of thin triangular plan-form wings and two rectangular wings in the 9-inch supersonic wind tunnel. The damping in roll of the rectangular wings was very close to what was predicted by linear theory, but the triangular wings gave results approximately 10 percent below that predicted when the wing leading edges were well ahead of or behind the Mach cone.
Date: February 17, 1949
Creator: Brown, Clinton E. & Heinke, Harry S., Jr.
Item Type: Refine your search to only Report
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Preliminary Study of Use of Nonstrategic Metals for and Application of Cooling to Blades of Turbine of J35 Turbojet Engine

Description: Memorandum presenting the modifications to the J35 engine that are necessitated with the use of non-strategic materials. Two proposals for cooling the rotor disk and blades are: finned hollow blades that are air cooled and blades with circular passages for liquid cooling in which the fuel could be used as the coolant.
Date: November 17, 1948
Creator: Turbine Cooling Research Branch
Item Type: Refine your search to only Report
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Free-Flight Investigation of the Rolling Effectiveness of a Wing-Spoiler Arrangement at High Subsonic, Transonic, and Supersonic Speeds

Description: Report presenting an investigation of the rolling effectiveness of a wing-spoiler arrangement using a rocket-propelled test vehicle in free flight. The configuration investigated in the report is likely not optimum and indicates a need for further exploration.
Date: May 17, 1948
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
open access

Ram-recovery characteristics of NACA submerged inlets at high subsonic speeds

Description: From Summary: "Results are presented of an experimental investigation of the characteristics of NACA submerged inlets on a model of a fighter airplane for Mach numbers from 0.30 to 0.875. The effects on the ram-recovery ratio at the inlets of Mach number, angle of attack, boundary-layer thickness on the fuselage, inlet location, and boundary-layer deflectors are shown. The data indicate only a slight decrease in ram-recovery ratio for the inlets ahead of or just behind the wing leading edge as … more
Date: November 17, 1948
Creator: Hall, Charles F. & Frank, Joseph L.
Item Type: Refine your search to only Report
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Control requirements and control parameters for a ram jet with variable-area exhaust nozzle

Description: Report presenting control requirements and parameters for a ram jet with a variable-area exhaust nozzle, which have been analyzed from calculated performance charts covering flight Mach numbers from 0.6 to 3.0 and altitudes from sea level to 30,000 feet. Requirements for maximum efficiency, safe and stable operation, maximum range of thrust at a given flight Mach number, and control of fuel flow are discussed and control parameters are selected.
Date: November 17, 1948
Creator: Boksenbom, Aaron S. & Novik, David
Item Type: Refine your search to only Report
open access

The Effect of Rear Chine Strips on the Take-Off Characteristics of a High-Speed Airplane Fitted With NACA Hydro-Skis

Description: "Results are presented from tank take-off tests of a dynamic model of a hypothetical high-speed airplane fitted with NACA hydro-skis and having the transverse curvature of the lower rear portion of the fuselage broken by small longitudinal chine strips. For the configuration tested, both trim and resistance were considerably reduced by the addition of the strips from the speed at which the ski emerged to the speed at which the rear of the fuselage came clear of the water. The results indicate t… more
Date: March 17, 1949
Creator: Ramsen, John A.
Item Type: Refine your search to only Report
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Control during starting of gas-turbine engines

Description: Report presenting an investigation of the variables pertinent to the control of gas temperatures of gas-turbine engines during starting conducted by obtaining time records of the variables involved during actual starting conditions. Poor control of gas temperatures during starting was found to be caused by an accumulation of fuel in the engine before ignition and excessive fuel-flow rates at the time of ignition.
Date: June 17, 1948
Creator: Koenig, Robert J. & Dandois, Marcel
Item Type: Refine your search to only Report
open access

Qualitative Measurements of Relative Flap Effectiveness at Transonic Speeds on a Series of Five Thin Airfoils With 25-Percent-Chord Flaps and Various Amounts of Sweepback

Description: Report presenting testing on a series of five flat plate models of aspect ratio 2.0 with 25-percent-mean-aerodynamic-chord flaps at a range of Mach numbers in order to investigate the effect of sweepback on flap effectiveness.
Date: May 17, 1948
Creator: Crane, Harold L. & McLaughlin, Milton D.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of an NACA 23012 Airfoil With 30 Percent-Chord Venetian-Blind Flaps

Description: Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of a NACA 23012 airfoil with 30-percent-chord venetian-blind flaps having one, two, three, and four slats of Clark y section. The three-slat arrangements was aerodynamically the best of those tested but showed practically no improvement over the comparable arrangement used in the preliminary tests published in NACA Technical Report No. 689. The multiple-slat flaps gave slightly higher lift coefficients tha… more
Date: September 17, 1941
Creator: Rogallo, F. M. & Spano, Bartholomew S.
Item Type: Refine your search to only Report
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