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Quarterly Report October, November and December, 1956

Description: Methods of producing extremely clean surfaces on rolled Zircaloy-2 strip have been investigated. It has been found that the finer abrasives, 400 mesh or finer, are more effective than coarse types because of their ability to penetrate pits and crevices more readily. Two such cleanings, with an intermediate 35 v/o HNO3-5 v/o HF pickle, resulted in a microscopically clean surface. Ultrasonic inspection of the EBWR fuel plates has been completed during this quarter. Approximately 95% of the plates… more
Date: December 31, 1956
Creator: Foote, Frank G.; Schumar, James F. & Chiswik, Haim H.
Item Type: Refine your search to only Report
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Altitude performance of J71-A-2(600-D1) turbojet engine

Description: From Introduction: "As part of a complete investigation of the J71-A-2(600-D1) turbojet engine conducted in an altitude test chamber at the NACA Lewis laboratory, the steady-state altitude performance, with afterburner inoperative and ejector shroud removed, was obtained and is presented herein. The component performance of the J71-A-2(600-D1) turbojet engine is presented in reference 1. The effects of compressor interstage bleed and adjustable inlet guide vanes on compressor-stall characterist… more
Date: December 28, 1956
Creator: Smith, Ivan D. & Sivo, Joseph N.
Item Type: Refine your search to only Report
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Component performance of J71-A-2(600-D1) turbojet engine at several Reynolds number indices

Description: Report presenting an investigation in the altitude test chamber to determine the altitude performance of the J71-A-2(600-D1) turbojet engine. The engine was equipped with two-position inlet guide vanes and compressor acceleration bleeds. Results regarding the compressor performance, combustor performance, turbine performance, and effect of altitude on engine performance are provided.
Date: December 28, 1956
Creator: Seashore, Ferris L. & Corrington, Lester C.
Item Type: Refine your search to only Report
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Performance of a blunt-lip side inlet with ramp bleed, bypass, and a long constant-area duct ahead of the engine : Mach number 0.66 and 1.5 to 2.1

Description: Unsteady shock-induced separation of the ramp boundary layer was reduced and stabilized more effectively by external perforations than by external or internal slots. At Mach 2.0 peak total-pressure recovery was increased from 0.802 to 0.89 and stable mass-flow range was increased 185 percent over that for the solid ramp. Peak pressure recovery occurred just before instability. The 7 and one-third-diameter duct ahead of the engine reduced large total-pressure distortions but was not as successfu… more
Date: December 28, 1956
Creator: Allen, John L.
Item Type: Refine your search to only Report
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Performance of a Blunt-lip Side Inlet With Ramp Bleed, Bypass, and a Long Constant-area Duct Ahead of the Engine- Mach Numbers 0.66 and 1.5 to 2.1

Description: Report presenting the performance of a side inlet with a fixed 12 degree two-dimensional compression surface for a range of Mach numbers, angles of attack, and yaw. The effects of several methods of compression-surface boundary-layer removal were investigated as well as a solid ramp.
Date: December 28, 1956
Creator: Allen, John L.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of the Interference Effects during Separation of a 1/40-Scale Model Convair B-58 Airplane and Store at Mach Numbers of 1.41, 1.61, and 2.01

Description: "An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a 1/40-sca!e pod-separation model of the Convair B-58 airplane at Mach numbers of 1.41, 1.61, and 2.01. The complete return component and the complete pod with its canard controls were tested, both alone and in the presence of each other, at Mach numbers of 1.61 and 2.01. The complete pod and various combinations of its components were tested alone at Mach numbe… more
Date: December 28, 1956
Creator: Driver, Cornelius
Item Type: Refine your search to only Report
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Static Stability and Control Characteristics of a 0.04956-Scale-Model of the Convair F-102A Airplane at Transonic Speeds

Description: Memorandum presenting the effects of elevator deflections from 0 to -10 degrees on the force and moment characteristics of a 0.04956-scale model of the Convair F-102A airplane at a range of Mach numbers and angles of attack. The model was tested with a plane wing to indicate the effects of wing leading-edge camber and deflected tips. The results indicated that the configuration was longitudinally stable for all conditions tested, but a possible mild pitch-up tendency was indicated for a lift co… more
Date: December 27, 1956
Creator: Olstad, Walter B. & Osborne, Robert S.
Item Type: Refine your search to only Report
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Experimental Study and Analysis of Loading and Pressure Distributions on Delta Wings Due to Thickness and to Angle of Attack at Supersonic Speeds

Description: Memorandum presenting the aerodynamic loading on delta wings at supersonic speeds, which was studied primarily to determine the coupling and nonlinear interference effects between the pressures due to angle of attack and due to thickness. Results regarding span loadings and lift coefficients, pressure distributions due to thickness, pressure distributions due to angle of attack and interference pressures produced by thickness, and Reynolds number effects are provided.
Date: December 26, 1956
Creator: Boatright, William B.
Item Type: Refine your search to only Report
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An Investigation of Ejection Releases of Submerged and Semisubmerged Dynamically Scaled Stores From a Simulated Bomb Bay of a Fighter-Bomber Airplane at Supersonic Speeds

Description: Report presenting an investigation of the release characteristics of several dynamically scaled store shapes from a simulated bomb bay at Mach numbers of 1.39, 1.60, and 1.98. A streamline store, a blunt-nose store with wedge-type fins of low aspect ratio, and a bluff store with a skirt were tested. Results regarding pitching motions, ejection velocity, effect of increase in altitude, and addition of plate or spike to the nose of the store are provided.
Date: December 26, 1956
Creator: Lee, John B. & Carter, Howard S.
Item Type: Refine your search to only Report
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An Investigation of Ejection Releases of Submerged and Semisubmerged Dynamically Scaled Stores from a Simulated Bomb Bay of a Fighter-Bomber Airplane at Supersonic Speeds

Description: Memorandum presenting an investigation in the 27- by 27-inch preflight jet on the release characteristics of several dynamically scaled store shapes from a simulated bomb bay at Mach numbers of 1.30, 1.60, and 1.98. A model of a typical fighter-bomber airplane with high sweptback wings was used. Results for streamline store A, blunt-nose store B, and bluff store C are provided.
Date: December 26, 1956
Creator: Lee, John B. & Carter, Howard S.
Item Type: Refine your search to only Report
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Investigation of the Ejection Release of Several Dynamically Scaled Bluff Internal Stores at Mach Numbers of 0.8, 1.39, and 1.98

Description: Report presenting an investigation to determine flight behavior after ejection from a bomb bay of several dynamically scaled bluff internal stores for a range of Mach numbers and altitudes. The trajectories of all of the stores were smooth, but the pitching motions of the stores were greatly affected by the close vicinity of the bomb bay. Types of stores explored included WADC stores, flared-cylinder stores, and cylindrical stores.
Date: December 26, 1956
Creator: Carter, Howard S. & Lee, John B.
Item Type: Refine your search to only Report
open access

Wind Tunnel Investigation at Low Speed of Aerodynamic Characteristics of Army Chemical Corps Model E-112 Bomblets with Span Chord Ratio of 2 - 1

Description: "An experimental investigation has been made in the Langley stability tunnel to determine the aerodynamic characteristics of the Army Chemical Corps model E-112 bomblets with span-chord ratio of 2:1. A detailed analysis has not been made; however, the results showed that all the models were spirally unstable and that a large gap between the model tips and end plates tended to reduce the instability" (p. 1).
Date: December 26, 1956
Creator: Letko, William
Item Type: Refine your search to only Report
open access

Efficiency of a Three Inch Higgins Column

Description: The following report describes the usage of a semi-continuous ion exchange contactor--named the Higgins contactor--fit to operate the Purex process, a process that recovers plutonium and uranium from irradiated natural uranium fuel elements. It is intended to use the contactor in the final purification and concentration stage of the process plutonium streams.
Date: December 20, 1956
Creator: Vaughan, Victor C.; Jansen, George & Bagley, Raymond O.
Item Type: Refine your search to only Report
open access

Fundamental flame velocity, heat of combustion, and spontaneous ignition temperature of dimethylaminodiborane

Description: The following properties have been determined for a sample of dimethylaminodiborane : (1) maximum fundamental flame velocity for fuel and air at 35 degrees C, 115 +/- 5 centimeters per second ; (2) net (lower) heat of combustion of liquid fuel to gaseous nitrogen, carbon dioxide, and water, and to solid boric oxide, 19,225 +/- 100 Btu per pound ; and (3) spontaneous ignition temperature, 240 degrees +/- 10 degrees F.
Date: December 19, 1956
Creator: Hibbard, Robert R. & Dugger, Gordon L.
Item Type: Refine your search to only Report
open access

An investigation of the lift, drag, and static-stability characteristics of a triangular-wing airplane configuration at Mach numbers from 3.00 to 6.28

Description: Report presenting lift, drag, and static-stability characteristics of a triangular-wing airplane over a range of Mach numbers, angles of attack, and angles of sideslip. The basic test configuration had values of maximum lift-drag ratios that were comparable to those obtained in previous tests of several airplane configurations designed primarily from considerations of flight at high supersonic speeds.
Date: December 19, 1956
Creator: Gloria, Hermilo R.
Item Type: Refine your search to only Report
open access

Preliminary investigation of methods to increase base pressure of plug nozzles at Mach 0.9

Description: The effects of various afterbody changes on the base pressure of a nacelle-type isentropic plug nozzle installation operating at lower-than-design jet pressure ratios were investigated at a Mach number of 0.9. Although the estimates of the net propulsive force contain some uncertainties, the results indicate that both a plain-ring base shroud and a circular-arc boattail fairing reduced the loss in net propulsive force experienced with a cylindrical nacelle installation of the plug nozzle.
Date: December 19, 1956
Creator: Salmi, Reino J.
Item Type: Refine your search to only Report
open access

Tank investigation of a series of related hydro-skis as load-alleviation devices for landing a seaplane in waves

Description: Report presenting a tank investigation to determine the effects of hydro-skis as load-alleviation devices for landing a seaplane in waves. Results regarding the basic model without hydro-ski, effect of longitudinal location of hydro-ski, effect of landing trim, effect of hydro-ski dimensions, effect of landing speed, effect of vertical location of hydro-ski, effect of wave height, effect of angle of incidence, effect of aerodynamic stability, and consideration of hydro-skis as a ditching aid ar… more
Date: December 19, 1956
Creator: Carter, Arthur W.; Morse, Archibald E., Jr. & Woodward, David R.
Item Type: Refine your search to only Report
open access

Thermal Stability of Pentaborane in the Range 329 to 419 Degrees F

Description: "The thermal stability of pentaborane has been determined in the temperature range 329 degrees to 419 degrees Fahrenheit by measuring the increase with time in the formation of nonvolatile residue. A relationship was established between the thermal stability and the temperature. The expression permitted extrapolation to obtain the stability of pentaborane at either high temperatures and short times or at ambient temperatures and long times" (p. 1).
Date: December 19, 1956
Creator: McDonald, Glen E.
Item Type: Refine your search to only Report
open access

Some Design and Operational Considerations of a Liquid-Hydrogen Fuel and Heat-Sink System for Turbojet-Engine Tests

Description: Memorandum presenting an experimental investigation in which liquid hydrogen was used as a heat sink for turbine-cooling in a high-temperature turbojet engine. Several problems were revealed which will require special attention in future work. The primary issue was pressure surging in the fuel system, which presented a problem in flow measurement and control.
Date: December 18, 1956
Creator: Corrington, Lester C.; Thornbury, Kenneth L. & Hennings, Glen
Item Type: Refine your search to only Report
open access

Measurement of Static Pressure on Aircraft

Description: "Existing data on the errors involved in the measurement of static pressure by means of static-pressure tubes and fuselage vents are presented. The errors associated with the various design features of static-pressure tubes are discussed for the condition of zero angle of attack and for the case where the tube is inclined to flow. Errors which result from variations in the configuration of static-pressure vents are also presented" (p. 645).
Date: December 17, 1956
Creator: Gracey, William
Item Type: Refine your search to only Report
open access

Chemical Properties of Sodium Triethylhydroborate and Sodium Triisopropoxyhydroborate

Description: Technical report abstract: Sodium hydride and triethylborane react to form sodium triethylhydroborate, NaBH(C2H5)3. This compound, a liquid at rooom temperature, was found to be soluble in hexane and mineral oil. A study was made of the thermal decomposition of sodium triethylhydroborate and its behavior toward boron trifluoride, boron trichloride, methyl borate, carbon dioxide, silane, and ethylene. Sodium triisopropoxyhydroborate, NaBH(OC3H7)3, was prepared and also found to be soluble in h… more
Date: December 13, 1956
Creator: Pearson, Richard King, 1926-; Edwards, L. J. & Maginnity, P. M.
Item Type: Refine your search to only Report
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