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The effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing

Description: "An investigation has been conducted in the Langley 300 MPH 7- by 10-foot tunnel to determine the effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing. Longitudinal and lateral stability characteristics were obtained for the model with and without tail surfaces" (p .1).
Date: December 6, 1948
Creator: Spearman, M. Leroy & Becht, Robert E.
Partner: UNT Libraries Government Documents Department
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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.
Partner: UNT Libraries Government Documents Department
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Pressure Distributions Over a Wing-Fuselage Model at Mach Numbers of 0.4 to 0.99 and at 1.2

Description: Report presenting pressure distributions over a prolate spheroid of fineness ratio 6 and over a combination of this body with an NACA 65-010 wing section for a range of Mach numbers. Results regarding wall and sting interference, nature of flow over a model in the transonic region, development of supersonic flow from subsonic flow, and a comparison of experimental and theoretical flow at subsonic stream Mach numbers are provided.
Date: November 3, 1948
Creator: Matthews, Clarence W.
Partner: UNT Libraries Government Documents Department
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Pressure Distributions on Thin Conical Body of Elliptic Cross Section at Mach Number 1.89

Description: Memorandum presenting an investigation conducted to determine the pressure distribution on a conical body of elliptic cross section at a Mach number of 1.89. Experimental data are presented for a range of angles of yaw from -16 to 16 degrees and angles of attack from -10 to 10 degrees. As the angle of flow deflection was increased, the deviation from experiment of the theoretical pressure distribution slightly increased, although agreement was satisfactory over the entire range of calculations.
Date: January 20, 1949
Creator: Maslen, Stephen H.
Partner: UNT Libraries Government Documents Department
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Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9 1 - Wing Tip With Subsonic Leading Edge

Description: An investigation was conducted at a Mach number of 1.91 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic leading edge swept back at 70 degrees. Except for pressure distribution on the top surface in the immediate vicinity of the subsonic leading edge, the maximum difference between linearized theory and experimental data was 2 1/2 percent (of free-stream dynamic pressure) for angles of attack up to 4 degrees and 7 percent for angles of attack up to 8 degrees. Pressures on the top surface nearest the subsonic edge indicated local expansions beyond values predicted by linearized theory.
Date: January 27, 1949
Creator: Jagger, James M. & Mirels, Harold
Partner: UNT Libraries Government Documents Department
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Longitudinal-Stability Investigation of High-Lift and Stall-Control Devices on a 52 Degree Sweptback Wing With and Without Fuselage and Horizontal Tail at a Reynolds Number of 6.8 X 10 (Exp 6)

Description: Contains low-speed longitudinal stability characteristics of a 52 degree sweptback wing of aspect ratio 2.88, taper ratio 0.625, and NACA 64 (sub 1)-112 airfoil sections normal to the 0.282-chord line, in combination with split flaps, leading-edge flaps, and upper-surface fences. Low-wing and midwing-fuselage aerodynamic characteristics are presented with and without a horizontal tail at various vertical locations. Tests were conducted at a Reynolds number of 6.8 x 10(exp 6).
Date: December 20, 1948
Creator: Foster, Gerald V. & Fitzpatrick, James E.
Partner: UNT Libraries Government Documents Department
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Flight and Wind-Tunnel Investigation to Determine the Aileron-Vibration Characteristics of 1/4-Scale Wing Panels of the Douglas D-558-2 Research Airplane

Description: Report presenting a flight and wind-tunnel investigation to determine the aerodynamic vibration characteristics of ailerons for the Douglas D-558-2 airplane. Testing was conducted to investigate the possibilities of a single-degree-of-freedom flutter known as aileron "buzz" or aileron compressibility flutter. Results regarding the three types of aileron vibration observed and vibration amplitudes are provided.
Date: November 30, 1948
Creator: Angle, Ellwyn E. & Lundstrom, Reginald R.
Partner: UNT Libraries Government Documents Department
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An analytical method of estimating turbine performance

Description: From Introduction: "An analytical method for estimating turbine performance from the blade angle8 and flow areas was therefore developed at the NACA Lewis laboratory and is described herein."
Date: December 29, 1948
Creator: Kochendorfer, Fred D. & Nettles, J. Cary
Partner: UNT Libraries Government Documents Department
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NACA Investigation of Fuels Corresponding to Specification an-F-58 : Results of Studies in Single Combustors of J-33, J-34, J-35, and Nene Turbojet Engines

Description: "The NACA is engaged in a program to evaluate the performance of fuels conforming to AN-F-58 specification in both full-scale engines and single combustors. This research memorandum constitutes an interim report on the results obtained on single cosibustors" (p. 1).
Date: November 16, 1945
Creator: Cleveland Laboratory Staff
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Flying-Boat Hulls Having Length-Beam Ratios of 20 and 30

Description: Report discussing the aerodynamic effects of length-beam ratios 20 and 30 as compared to length-beam ratios from 6 to 15. There was slightly more longitudinal stability and slightly less directional stability than in the lower ratios and not much change in the minimum drag coefficient.
Date: November 10, 1948
Creator: Riebe, John M.
Partner: UNT Libraries Government Documents Department
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Effect of Centrifugal Force on Critical Flutter Speed on a Uniform Cantilever Beam

Description: Report presenting theoretical calculations made by means of semirigid-flutter theory to determine the effect of centrifugal force on the critical flutter speed of a uniform cantilever beam. Calculations are made on airfoils with fundamental bending frequencies up to 2000 radian per second. Centrifugal force can under certain conditions reduce the critical flutter speed.
Date: June 18, 1948
Creator: Mendelson, Alexander
Partner: UNT Libraries Government Documents Department
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The Subsonic Aerodynamic Characteristics of Two Double-Wedge Airfoil Sections Suitable for Supersonic Flight

Description: Memorandum presenting high-speed wind-tunnel testing to investigate the aerodynamic characteristics at subsonic speeds of two symmetrical double-wedge airfoil sections of 4- and 6-percent-chord thickness suitable for application to supersonic aircraft. Section coefficients of lift, drag, and quarter-chord pitching moment are presented for a moderate range of angles of attack at Mach numbers up to approximately 0.93. The double-wedge airfoil exhibits no characteristics other than those common to the usual subsonic profile which would contribute to unsteady or uncontrollable flight at subsonic speeds of aircraft employing such a section for lifting surfaces.
Date: May 12, 1947
Creator: Solomon, Joseph & Henney, Floyd W.
Partner: UNT Libraries Government Documents Department
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The Linear Perturbation Theory of Axially Symmetric Compressible Flow With Application to the Effect of Compressibility on the Pressure Coefficient at the Surface of a Body of Revolution

Description: Memorandum discussing four related methods for the study of compressible flow by means of the linear perturbation theory for the case of three-dimensional flow with axial symmetry. A general method which includes the other is also discussed briefly. In each case, the properties of the compressible flow are obtained from those of a corresponding incompressible flow.
Date: July 18, 1947
Creator: Herriot, John G.
Partner: UNT Libraries Government Documents Department
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Comparative Drag Measurements at Transonic Speeds of an NACA 65-006 Airfoil and a Symmetrical Circular-Arc Airfoil

Description: Report presenting measurements made at transonic speeds by the freely-falling-body method to compare the drag of a rectangular plan-form airfoil of aspect ratio 7.6 with an NACA 65-006 airfoil section. Results regarding the velocity measurements, base-pressure measurements, and airfoil drag measurements are provided.
Date: March 6, 1947
Creator: Thompson, Jim Rogers & Marschner, Bernard W.
Partner: UNT Libraries Government Documents Department
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Comparison of National Bureau of Standards ceramic coatings L-7C and A-417 on turbine blades in a turbojet engine

Description: Report presenting an investigation to determine which of two ceramic coatings, L-7C and A-417, developed by the National Bureau of Standards is more suitable as a protective coating for turbine blades in a turbojet engine. Four cast Vitallium turbine blades, two coated with each of the ceramics, were installed in a turbine wheel of a turbojet engine and subjected to accelerated cyclic life tests.
Date: December 22, 1948
Creator: Morse, C. Robert
Partner: UNT Libraries Government Documents Department
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Free-Flight Investigation of Control Effectiveness of Full-Span 0.2-Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Section Thickness and Wing Sweepback

Description: Report discusses the development and testing of a rocket-propelled test vehicle to investigate aerodynamic control effectiveness at high subsonic, transonic, and supersonic speeds. Modifications to the section thickness and wing sweepback to improve performance are also described. A description of the vehicle, instrumentation, accuracy, and evaluation of testing results is included.
Date: May 29, 1947
Creator: Sandahl, Carl A. & Marino, Alfred A.
Partner: UNT Libraries Government Documents Department
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An Investigation of the Low-Speed Characteristics of Two Sharp-Edge Supersonic Inlets Designed for Essentially External Supersonic Compression

Description: Report presenting an investigation of two sharp-edge annular inlets with conical central bodies at low airspeeds in the propeller research tunnel to obtain information concerning the surface-pressure, drag, and pressure-recovery characteristics of the inlets at subsonic flight. Results regarding the nose and inner surface of the diffuser, inlet lips, minimum surface pressures and critical Mach numbers, pressure surveys in inlets, and pressure surveys in diffusers are provided.
Date: June 6, 1947
Creator: Dennard, John S.
Partner: UNT Libraries Government Documents Department
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Estimation of Lift and Drag of Airfoils at Near Sonic Speeds and in the Presence of Detached Shock Waves

Description: Report presenting a semiempirical method of estimating the forces on airfoil at near sonic speeds and in the presence of detached shock waves. The calculated values were found to be in good agreement with wind-tunnel testing of the forces on sharp-nose airfoils and two-dimensional wings.
Date: February 23, 1949
Creator: Mayer, John P.
Partner: UNT Libraries Government Documents Department
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Measurements of the damping in roll of large-scale swept-forward and swept-back wings

Description: Report presenting wind-tunnel testing of five large-scale tapered wings with a variety of angles of sweep to determine the effects of scale and sweep on the damping-in-roll parameter. Rolling moment and pressure distribution were measured for each plain wing while in steady roll for a range of angles of attack. Results regarding the effects of sweep at zero lift, effects of lift, and aurorotational characteristics are provided.
Date: July 30, 1947
Creator: Hunton, Lynn W. & Dew, Joseph K.
Partner: UNT Libraries Government Documents Department
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Theoretical and Experimental Analysis of Low-Drag Supersonic Inlets Having a Circular Cross Section and a Central Body at Mach Numbers of 3.30, 2.75, and 2.45

Description: Memorandum presenting a discussion of inlets with a circular cross section and a central body designed for high Mach numbers. The optimum proportion between external and internal supersonic compression is discussed in relation to the external drag and the maximum pressure recovery. Results and analysis regarding the maximum pressure recovery as a function of the cowling position parameter, the effect of the cone angle parameter on the maximum pressure recovery obtained, the highest pressure recovery obtained as a function of the central-body-diameter parameter, the maximum pressure recovery as a function of Mach number, and optical observations of the flow phenomena about the inlets are provided.
Date: November 10, 1948
Creator: Ferri, Antonio & Nucci, Louis M.
Partner: UNT Libraries Government Documents Department
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Investigation of Suction Slot Shapes for Controlling a Turbulent Boundary Layer

Description: Report presenting testing of several boundary-layer-control suction slots in a two-dimensional diffuser to develop design criteria and to evaluate the practical minimum total-pressure losses. The shape of the boundary layer behind the slot was found to depend only on the quantity of air removed provided the slot inert had rounded edges.
Date: 1956
Creator: Pierpont, P. Kenneth
Partner: UNT Libraries Government Documents Department
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The use of perforated inlets for efficient supersonic diffusion

Description: Report presenting the use of wall perforations on supersonic diffusers to avoid the internal contraction-ratio limitation. Experimental results on a preliminary model of a perforated diffuser at Mach number 1.85 are provided. A theoretical discussion of the flow coefficients and the size and spacing of the perforations are included.
Date: June 25, 1947
Creator: Evvard, John C. & Blakey, John W.
Partner: UNT Libraries Government Documents Department
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Comparison of flight performance of AN-F-58 and AN-F-32 fuels in J35 turbojet engine

Description: Report presenting a flight investigation to determine the comparative performance of AN-F-58 and AN-F-32 fuels in a 4000-pound-thrust turbojet engine. The fuels were equivalent over the range of conditions investigated. Results regarding corrected net thrust, corrected jet-fuel consumption, variation of corrected tail-pipe temperature, combustor blow-out speeds, and visual observations of the jet exhaust are provided.
Date: April 7, 1949
Creator: Acker, Loren W. & Kleinknecht, Kenneth S.
Partner: UNT Libraries Government Documents Department
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An Investigation of the Characteristics of Three NACA 1-Series Nose Inlets at Subcritical and Supercritical Mach Numbers

Description: Report presenting an investigation of the characteristics of three representative NACA 1-series nose inlets over a Mach number range extending from 0.4 to 0.925 in the high-speed wind tunnel. Results regarding pressure distribution, drag, and some potential design considerations are provided.
Date: January 13, 1949
Creator: Pendley, Robert E. & Smith, Norman F.
Partner: UNT Libraries Government Documents Department
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