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Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds

Description: Memorandum presenting force and moment characteristics of configurations employing wings of very low aspect ratio as determined for Mach numbers of 1.97 and 3.33. The angle of attack range was from 0 to 17 degrees for Mach number 1.97 and from 0 to 30 degrees for Mach number 3.33. Results regarding experimental force and moment characteristics, comparisons of theoretical and experimental force and moment characteristics, and visual observations of flow over models are provided.
Date: October 26, 1956
Creator: Jorgensen, Leland H. & Katzen, Elliott D.
Partner: UNT Libraries Government Documents Department
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The Effect of Blunt-Trailing-Edge Modifications on the High-Speed Stability and Control Characteristics of a Swept-Wing Fighter Airplane

Description: An investigation was conducted on a 35 deg swept-wing fighter airplane to determine the effects of several blunt-trailing-edge modifications to the wing and tail on the high-speed stability and control characteristics and tracking performance. The results indicated significant improvement in the pitch-up characteristics for the blunt-aileron configuration at Mach numbers around 0.90. As a result of increased effectiveness of the blunt-trailing-edge aileron, the roll-off, customarily experienced with the unmodified airplane in wings-level flight between Mach numbers of about 0.9 and 1.0 was eliminated, The results also indicated that the increased effectiveness of the blunt aileron more than offset the large associated aileron hinge moment, resulting in significant improvement in the rolling performance at Mach numbers between 0.85 and 1.0. It appeared from these results that the tracking performance with the blunt-aileron configuration in the pitch-up and buffeting flight region at high Mach numbers was considerably improved over that of the unmodified airplane; however, the tracking errors of 8 to 15 mils were definitely unsatisfactory. A drag increment of about O.OOl5 due to the blunt ailerons was noted at Mach numbers to about 0.85. The drag increment was 0 at Mach numbers above 0.90.
Date: May 26, 1954
Creator: Sadoff, Melvin; Matteson, Frederick H. & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department
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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.
Partner: UNT Libraries Government Documents Department
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Induction System Characteristics and Engine Surge Occurrence for Two Fighter-Type Airplanes

Description: Memorandum presenting an investigation conducted to measure and compare the total-pressure recovery and distortion characteristics at the compressor face of two single-place fighter-type airplanes with similar two-spool turbojet engines, but with dissimilar inlets. The total-pressure recovery was relatively independent of angle of attack and mass-flow ratio for both airplanes except for a significant decrease in pressure recovery with angle of attack for airplane B at the highest Mach numbers tested.
Date: May 26, 1958
Creator: Larson, Terry J.; Thomas, George M. & Bellman, Donald R.
Partner: UNT Libraries Government Documents Department
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Fabrication and Properties of Hot-Pressed Molybdenum Disilicide

Description: Report presenting an investigation of hot-pressed molbdenum disilicide bodies produced by industrial processes at a temperature of 2950 degrees and a pressure of 3000 pounds per square inch. Results regarding the short-time tensile strength, stress-rupture data, compression strength, air-corrosion resistance, hardness, coefficient of linear thermal expansion, thermal conductivity, and density are provided.
Date: May 26, 1950
Creator: Long, Roger A.
Partner: UNT Libraries Government Documents Department
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Investigation of a 1/22-Scale of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Static Longitudinal Stability and Control and Performance Characteristics at Transonic Speeds

Description: Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 in the transonic tunnel at Mach numbers from 0.60 to 1.13. Results in this report include the static longitudinal stability and control characteristics, the effect of various configuration modifications on lift-drag ratio, the effect of subsonic and supersonic inlets and external stores, and the effect of area-distribution modifications on performance.
Date: April 26, 1956
Creator: Luoma, Arvo A.
Partner: UNT Libraries Government Documents Department
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Preliminary Evaluation of Flight-Weight XRJ47-W-5 Ram-Jet Engine at a Mach Number of 2.75

Description: Report presenting a free-jet investigation of the performance, burner-shell cooling, and ignition characteristics of a flight-weight 48-inch-diameter XRJ47-W-5 ramjet engine at an inlet Mach number of 2.75 and an angle of attack of 3 degrees. Data were obtained over a range of altitudes, inlet temperatures, and fuel-air ratios.
Date: July 26, 1955
Creator: Welna, Harry J. & Reilly, Dwight H.
Partner: UNT Libraries Government Documents Department
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Investigation of High-Angle-of-Attack Performance of a 14 Deg Ramp-Type Inlet in Various Circumferential Body Locations: Mach Number Range 1.5 to 2.0

Description: Memorandum presenting an investigation to determine the internal flow performance of a fixed 14 degree ramp inlet from zero to 20 degrees angle of attack conducted at three free-stream Mach numbers. The inlet was mounted in three circumferential fuselage locations and utilized inlet throat and fuselage boundary-layer removal.
Date: June 26, 1957
Creator: Mitchell, Glenn A. & Chiccine, Bruce G.
Partner: UNT Libraries Government Documents Department
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Measurement of distortion in second experimental control rod for argonne naval reactor with constant transverse temperature gradient and uniform longitudinal temperature distribution

Description: Report presenting measurements of the thermal distortion of a stainless-steel clad, cadmium-silver reactor control rod. The temperature pattern of the rod is described. The maximum reduction in clearance obtained in the tests was 0.203 inch.
Date: September 26, 1951
Creator: Nagey, T. F. & Lietzke, A. F.
Partner: UNT Libraries Government Documents Department
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Summary of the Lift, Drag, and Stability of 1/10-Scale Rocket-Boosted Models of the McDonnell XF3H-1 Airplane for a Mach Number Range of 0.6 to 1.4 as Affected by the Operation of Extensible Rocket Racks

Description: Report discussing an investigation of the McDonnell XF3H-1 with models to determine the aerodynamic effects of operating internally stowed extensible rocket racks during transonic flight. Information about the flutter, static longitudinal stability, dynamic longitudinal stability, static directional stability, trim, drag, and effect of rocket racks on aerodynamic characteristics of the model is provided.
Date: January 26, 1954
Creator: Crabill, Norman L. & McFall, John C., Jr.
Partner: UNT Libraries Government Documents Department
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Effects of Various Modifications on the Static Longitudinal Stability and Control Characteristics of a 0.065-Scale Model of the Chance Vought Regulus II Missile at a Mach Number of 2.01

Description: "An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects on the static longitudinal stability and control characteristics of various modifications to a 0.065-scale model of the Chance Vought Regulus II missile. The modifications consisted of a control housing on top of the fuselage, two sizes of canard surfaces with fixed incidence angles, various angles of nose droop, and two types of inlet boundary-layer bleed diverters. The tests were made at a Mach number of 2.01 and a Reynolds number, based on the mean aerodynamic chord of 1.54 x 10(exp 6)" (p. 1).
Date: September 26, 1955
Creator: Robinson, Ross B. & Driver, Cornelius
Partner: UNT Libraries Government Documents Department
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Analytical Investigation of Fuel-Cooled Turbine Blades With Return-Flow Type of Finned Coolant Passages

Description: Memorandum presenting an investigation of coolant-flow rates for a turbine rotor blade with return-flow type of coolant-passage configuration formed by fins within a capped blade shell with both hydrogen and methane fuels as coolants. Results regarding spanwise blade and coolant temperature distributions, effects of coolant inlet temperature on hydrogen-coolant-flow requirements, comparison of return-flow-blade coolant requirements, effect of fin thickness and fin height, comparison of hydrogen and methane as coolants, and feasibility of fuel-cooled turbines are provided.
Date: June 26, 1957
Creator: Nachtigall, Alfred J. & Slone, Henry O.
Partner: UNT Libraries Government Documents Department
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A review of instruments developed for the measurement of the meteorological factors conductive to aircraft icing

Description: Report presenting a review of the status of instruments suitable for the measurement of the meteorological factors conducive to aircraft icing. Nine instruments which appear to be the most promising for obtaining meteorological data are discussed and recommendations for their continued use and development are provided.
Date: April 26, 1949
Creator: Jones, Alun R. & Lewis, William
Partner: UNT Libraries Government Documents Department
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Preliminary Wind-Tunnel Investigation of the Effect of Area Suction on the Laminar Boundary Layer Over an NACA 64A010 Airfoil

Description: Memorandum presenting a preliminary investigation made in the two-dimensional low-turbulence tunnel on an NACA 64A010 airfoil with permeable surfaces to obtain an indication of the stabilizing effect of area suction on the laminar boundary layer. Although the airfoil surface had many waves and irregularities of contour, the data corroborated qualitatively the theoretically predicted stabilizing effect of area suction on a smooth flat plate.
Date: April 26, 1948
Creator: Braslow, Albert L.; Visconti, Fioravante & Burrows, Dale L.
Partner: UNT Libraries Government Documents Department
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Pressure Distributions and Aerodynamic Characteristics of Several Spoiler-type Controls on a Trapezoidal Wing at Mach Numbers of 1.61 and 2.01

Description: Memorandum presenting an investigation at Mach numbers of 1.61 and 2.01 to examine the characteristics of a series of nine spoiler-type controls on a trapezoidal wing with the leading edge swept back 23 degrees, an aspect ratio of 3.1, and a taper ratio of 0.4. Results regarding pressure distributions, spanwise loadings, and integrated coefficients are provided.
Date: July 26, 1956
Creator: Lord, Douglas R. & Czarnecki, K. R.
Partner: UNT Libraries Government Documents Department
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Transonic Flight Evaluation of the Effects of Fuselage Extension and Indentation on the Drag of a 60-Degree Delta Wing Interceptor Airplane

Description: Report presenting the lift and drag characteristics of a 60-degree delta-wing interceptor airplane with fuselage extension and indentation at a range of Mach numbers and altitudes. A comparison with a prototype airplane and a comparison of the flight results with the model tests are provided.
Date: September 26, 1957
Creator: Saltzman, Edwin J. & Asher, William P.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of a Wing-Root Inlet Configuration With Various Modifications at Mach Numbers of 1.41, 1.81, and 2.01

Description: Memorandum presenting a wing-root inlet configuration in which inlet components were varied and was tested in the 4- by 4-foot supersonic pressure tunnel at 3 Mach numbers. Angles of attack and sideslip ranges were also varied. Inlet performance and engine-flow distortions as affected by pitch, sideslip, inlet-lip sweep, contraction ratio, boundary-layer control, and engine bypass are presented and discussed.
Date: September 26, 1957
Creator: Robins, A. Warner
Partner: UNT Libraries Government Documents Department
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Hydrogen for Turbojet and Ramjet Powered Flight

Description: Memorandum presenting various reports regarding the use of hydrogen for turbojet and ramjet powered flight. Some of the characteristics considered include the combustion properties, potential fueling problems, and flight experience with hydrogen on-board.
Date: April 26, 1957
Creator: Lewis Flight Propulsion Laboratory
Partner: UNT Libraries Government Documents Department
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Theoretical Analysis of the Interference Effects of Several Supersonic Tunnel Walls Capable of Absorbing the Shock Caused by the Nose of a Model

Description: Memorandum presenting a theoretical analysis of the supersonic flow about two-dimensional and three-dimensional axially symmetric models restricted by theoretical walls capable of removing the nose shock. Results regarding the supersonic-tunnel interference due to nonreflecting walls and supersonic-tunnel interference due to porous walls are provided.
Date: May 26, 1958
Creator: Matthews, Clarence W.
Partner: UNT Libraries Government Documents Department
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