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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 successful for small distortions as obtained with throat bleed. By removing boundary-layer air the bypass nearly recovered the total-pressure loss due to the long duct.
Date: December 28, 1956
Creator: Allen, John L.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

Production of Neutral Photopions as a Function of Atomic Weight

Description: Thesis discussing the relative yield of neutral pions from elements in a reaction "as a function of the quantum-limit energy (the maximum energy of the quanta in the bremsstrahlung beam) of the Berkeley synchrotron." Interpretation of the results leads to values for the mean free path for absorption of the neutral pions in nuclear matter.
Date: May 28, 1956
Creator: Anderson, John David
Partner: UNT Libraries Government Documents Department

Free-flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Deg Sweptback Wing of Aspect Ratio 4

Description: Free flight test of tailless missile configuration with 45-deg sweptback wing of aspect ratio 4 - stability at transonic speeds. The longitudinal flexible-wing results indicated a gradual transonic trim change a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5. Results regarding trim characteristics, lift and longitudinal stability, and side-force and lateral stability are provided.
Date: August 28, 1956
Creator: Arbic, Richard G.
Partner: UNT Libraries Government Documents Department

Free-Flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Degree Sweptback Wing of Aspect Ratio 4

Description: Memorandum presenting a flight test of a long-range missile configuration with a 45 degree sweptback wing of aspect ratio 4 conducted at a range of Mach and Reynolds numbers. The longitudinal flexible-wing results indicated a gradual transonic trim change and a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5.
Date: August 28, 1956
Creator: Arbic, Richard G.
Partner: UNT Libraries Government Documents Department

Experimental Investigation of a Transonic Axial-Flow-Compressor Rotor Designed for Sonic Inlet Velocity with an Inlet Hub-Tip Radius of 0.35

Description: Memorandum presenting a high-flow sonic-inlet compressor rotor employing double-circular-arc blade sections that was designed and tested in Freon-12. Results regarding overall performance, radial distribution, and blade-element performance are provided.
Date: September 28, 1956
Creator: Boxer, Emanuel & Bernot, Peter T.
Partner: UNT Libraries Government Documents Department

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 numbers of 1.41, 1.61, and 2.01 and also in the presence of the return component at Mach numbers of 1.61 and 2.01" (p. 1).
Date: December 28, 1956
Creator: Driver, Cornelius
Partner: UNT Libraries Government Documents Department

Differential Thermal Analysis of Uranium Tetrafluoride-Uranium Dioxide Mixtures

Description: Abstract: "Approximate melting points have been determined for five samples of uranium tetrafluoride representing incompletely converted uranium dioxide and covering the range from about 2 to 20 w/o UO2, using the method of differential thermal analysis. The results indicate the melting temperatures are in the range of 920 to 980 C. No significant correlation between melting point and UO2 content was observed, possibly because of calcite formation. Similar results were obtained on synthetic mistakes of UF4 containing from 10 to 40 w/o UO2."
Date: June 28, 1956
Creator: Ewing, Robert A. & Bearse, Arthur E.
Partner: UNT Libraries Government Documents Department

APPR-1 Axial Non-Uniform Burn Up--Initial Studies

Description: The control rod position in relation to reactor lifetime and the relative concentrations of U/sup 235/ and B/sup 10/ as a function of U burned were found by a modified 2-group theory using the adjusted age and a straight 2- group theory without fast multiplication or resonance capture. Results indicate that at 15% average burnup the flux shape and reactivity do not vary appreciably from that given by the uniform analysis. (F.S.)
Date: March 28, 1956
Creator: Fairbanks, F. B.
Partner: UNT Libraries Government Documents Department

Supersonic Investigation of the Lift, Drag, Static Stability, and Hinge-Moment Characteristics of a Rocket-Powered Model of a Ballistic-Missile Configuration

Description: Memorandum presenting a free-flight investigation to determine the lift, drag, static stability, and hinge-moment characteristics of a rocket-powered model of a rocket-powered model of a ballistic-missile configuration at supersonic speeds. The model consisted essentially of a body of fineness ratio 16.9 and a cruciform set of small 60 degree delta fins located approximately 1 body diameter from the base of the body. The model lift and pitching-moment coefficients were nonlinear with angle of attack.
Date: September 28, 1956
Creator: Gillespie, Warren, Jr.
Partner: UNT Libraries Government Documents Department

Supersonic Investigation of the Lift, Drag, Static Stability, and Hinge-Moment Characteristics of a Rocket-Powered Model of a Ballistic-Missile Configuration

Description: Report presenting a free-flight investigation to determine the lift, drag, static stability, and hinge-moment characteristics of a rocket-powered model of a ballistic-missile configuration. The purpose of this particular investigation was to determine these characteristics with a long run of boundary layer ahead of small 60 degree delta stabilizing fins.
Date: September 28, 1956
Creator: Gillespie, Warren, Jr.
Partner: UNT Libraries Government Documents Department

RESULTS OF PACKAGE BOILER TEST. HRT Test No. V 4a

Description: The package boiler was operated at a maximum steam rate of 1750 Ib/hr at 1500 psi. The operation of the pumps, relief valves, gages, and pressure controller was checked. The time required for the boiler to come up to full operation was 15 to 20 min. On the basis of the test the boiler is considered to meet the manufacturer's specifications. (auth)
Date: June 28, 1956
Creator: Gory, J L
Partner: UNT Libraries Government Documents Department

Hinge Moment and Effectiveness of an Unswept Constant-Chord Control and an Overhang-Balanced, Swept Hinge-Line Control on an 80 Degree Swept Pointed Wing at Mach Numbers from 0.75 to 1.96

Description: Memorandum presenting an investigation of a semispan-wing-fuselage model with an 80 degree swept pointed wing with either an unbalanced constant-chord control or an overhang-balanced swept hinge-line control in the 9- by 12-inch blowdown tunnel. Control hinge moments and effectiveness characteristics were obtained over an angle-of-attack range of plus or minus 16 degrees at control deflections up to 25 degrees. Results regarding control effectiveness, control hinge moments, control drag, and evaluation of control characteristics are provided.
Date: August 28, 1956
Creator: Guy, Lawrence D.
Partner: UNT Libraries Government Documents Department

Evaluation of Liquefied Hydrocarbon Gases as Turbojet Fuels

Description: Memorandum presenting an analysis of liquid methane, ethene, and propane along with normally liquid hydrocarbon fuels. The lower molecular weight hydrocarbons are superior to current JP-type fuels as heat sinks and that the more volatile fuels may be required with cooled-turbine engines.
Date: December 28, 1956
Creator: Hibbard, Robert R.
Partner: UNT Libraries Government Documents Department

Free-flight investigation over a Mach number range from 0.74 to 1.43 at lift coefficients from minus 0.15 to 0.75 of an airplane-configuration model having a 52.5 degree delta wing and a low swept horizontal tail

Description: Report presenting a free-flight investigation over a range of Mach numbers at a range of lift coefficients to determine the aerodynamic characteristics of an airplane-configuration model with a 52.5 degree delta wing and a low, swept horizontal tail. Results regarding time history, longitudinal trim, lift, drag, longitudinal static stability, side-force characteristics, and theoretical comparisons are provided.
Date: September 28, 1956
Creator: Kehlet, Alan B.
Partner: UNT Libraries Government Documents Department