Technical Report Archive & Image Library (TRAIL) - 35 Matching Results

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Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine IV: performance with tail-pipe burning and water injection

Description: From Introduction: "Thrust augmentation of an axial-flow-type turbojet engine by burning fuel in the tail pipe is discussed in references 1 to 3. Thrust augmentation of the same turbojet engine by water injection at the compressor inlet is reported in reference 4."
Date: June 15, 1948
Creator: Dietz, Robert O., Jr.; Wishnek, George & Kuenzig, John K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Hovering Performance of Helicopters Powered by Jet-Propulsion and Reciprocating Engines

Description: Report presenting an investigation of the maximum hovering time, or the time that a helicopter can sustain itself without motion, for helicopters using a reciprocating engine, by ramjet engines at the tips of rotor blades, and by pulse-jet engines at the tips of rotor blades. Testing showed that the reciprocating engine permitted much longer hovering time than the jet-propulsion engines, but the jet-propulsion engines were much lighter and could lift greater disposable loads.
Date: June 11, 1948
Creator: Brightwell, Virginia L.; Peters, Max D. & Sanders, J. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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
Partner: UNT Libraries Government Documents Department
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Effect of Aerodynamic Hysteresis on Critical Flutter Speed at Stall

Description: Memorandum presenting a theoretical analysis of the effect of aerodynamic hysteresis on stalling flutter. The results were applied to a given airfoil and correlation of the experimental and theoretical results was found possible by assuming that the angle of aerodynamic lag varies as the slope of the static-lift curve. It was shown that the phenomenon of stalling flutter can at least in some cases be explained on the basis of an aerodynamic lag or hysteresis effect.
Date: June 18, 1948
Creator: Mendelson, Alexander
Item Type: Refine your search to only Report
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
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effectiveness at High Speeds of a 10-Percent-Chord Plain Trailing-Edge Flap on the NACA 65-210 Airfoil Section

Description: This report contains the results of a high-speed wind-tunnel investigation of the effectiveness of a 10-percent-chord plain flap on the NACA 65-210 airfoil section. The results include an indication of the lift-producing characteristics and the effectiveness of the 10-percent-chord flap. From a comparison of the characteristics of the 10-percent-chord flap with those of a 20-percent-chord flap it was concluded that, although a reduction in flap-chord ratio from 0.20 to 0.10 lessens the severity… more
Date: June 14, 1948
Creator: Ilk, Richard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effects of Fuel Sloshing on the Lateral Stability of a Free-Flying Airplane Model

Description: Memorandum presenting an investigation in the free-flight tunnel to determine the effect of the sloshing of fuel in partly filled, unbaffled tanks on the lateral stability of a free-flying model. Flight tests were made to determine the effects of the water sloshing for different depths of water and various masses and moments of inertia of the model. The sloshing caused small-amplitude, high-frequency lateral oscillations which were superimposed on the normal Dutch roll oscillation so that the l… more
Date: June 29, 1948
Creator: Smith, Charles C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Equations for the Design of Two-Dimensional Supersonic Nozzles

Description: Memorandum presenting equations for obtaining the wall coordinates of two-dimensional supersonic nozzles. The equations are based on the application of the method of characteristics to irrotational flow of perfect gases in channels. A brief discussion of characteristics as applied to nozzle design is given to assist in understanding and applying the nozzle-design method of the report.
Date: June 21, 1948
Creator: Pinkel, I. Irving
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation at supersonic speeds of twin-scoop duct inlets of equal area 2: effects of slots upon an inlet enclosing 61.5 percent of the maximum circumference of the forebody

Description: Report presenting tests at Mach numbers between 1.36 and 2.01 of a twin-scoop duct inlet that had slots in the walls of the duct contiguous to the forebody and immediately behind the inlet. The mass flow and total-pressure recovery through the diffusor were measured during tests in which the slot length was constant and the slot width and ramp angle were varied. Results regarding mass flow and total-pressure recovery are provided.
Date: June 9, 1948
Creator: Davis, Wallace F. & Goldstein, David L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An experimental investigation of NACA submerged inlets at high subsonic speeds 1: inlets forward of the wing leading edge

Description: From Summary: "This report covers the first part of an experimental investigation of NACA submerged inlets at four locations on the fuselage of a fighter airplane model for Mach numbers from 0.30 to 0.875. Data are presented showing the characteristics of the model without inlets and with inlets 16.7 percent of the root chord forward of the wing-root leading edge and equipped with small boundary-layer deflectors. The data show that variations in the mass of air entering the inlet had a large ef… more
Date: June 9, 1948
Creator: Hall, Charles F. & Barclay, F. Dorn
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A flight investigation and analysis of the lateral-oscillation characteristics of an airplane

Description: Report presenting flight tests to determine the causes of undesirable dynamic lateral-stability characteristics of an airplane. Various rudder modifications were flight tested with the rudder free and fixed over an indicated airspeed range from approximately 200 to 450 miles per hour. Results regarding rudder-fixed characteristics and rudder-free characteristics are provided.
Date: June 3, 1948
Creator: Stough, Carl J. & Kauffman, William M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Force, Static Longitudinal Stability, and Control Characteristics of a 1/16-Scale Model of the Bell XS-1 Transonic Research Airplane at High Mach Numbers

Description: Report presenting results obtained to determine the effects of compressibility at high Mach numbers on a scale model of the Bell XS-1 transonic research airplane. The results are presented for several model configurations through a range of Mach numbers. Results regarding aerodynamic characteristics and static longitudinal stability characteristics are provided.
Date: June 23, 1948
Creator: Mattson, Axel T. & Loving, Donald L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning Characteristics of a 1/21-Scale Model of the Douglas AD-2W Airplane: TED No. NACA DE329

Description: Report presenting an investigation to determine the spin and recovery characteristics of a model of the Douglas AD-2W airplane, which has a large radome installation. Results indicated that the plane has satisfactory erect and inverted spin-recovery characteristics. Information about erect spins, inverted spins, and recommended recovery technique is provided.
Date: June 9, 1948
Creator: White, Richard P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A fuel-distribution control for gas-turbine engines

Description: "The principle of operation of a device to control the distribution of fuel to any number of discharge nozzles of a gas-turbine engine is presented. A description of an experimental model of the device and the results of a bench investigation are presented. This device controlled the flow to four discharge nozzles within 2 percent of perfect distribution over a wide range of fuel flow and was unaffected by uneven discharge-nozzle pressures" (p. 1).
Date: June 14, 1948
Creator: Gold, Harold & Straight, David M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-Speed Wind-Tunnel Investigation of a Flying-Boat Hull With High Length-Beam Ratio

Description: Report presenting the results of an investigation to determine the effect of Mach number on the aerodynamic characteristics of a flying-boat hull with a high length-beam ratio. Information about the drag coefficients, angles of attack for minimum drag, and longitudinal and directional stability is provided.
Date: June 30, 1948
Creator: Riebe, John M. & Naeseth, Rodger L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-Speed Wind-Tunnel Tests of a 1/16-Scale Model of the D-558 Research Airplane: D-588-1 Speed-Reduction Brake and Symmetrical-Profile Wing Characteristics

Description: Report presenting the results of pitching-moment, lift, and drag measurements on a model of the D-558-1 with speed reduction brakes and a symmetrical profile wing at a range of Mach numbers. Only a small decrement in Mach number is produced with no nose-inlet flow and the speed-reduction brakes deflected.
Date: June 15, 1948
Creator: Wright, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ice protection of turbojet engines by inertia separation of water 2: single-offset-duct system

Description: Investigation of a single-offset-duct system designed to prevent entrance of water into a turbojet engine was conducted on a half-scale nacelle model. An investigation was made to determine ram-pressure recovery and radial velocity profiles at the compressor section and icing characteristics of such a duct system. At a design inlet velocity of 0.77, the maximum ram-pressure recovery attained with effective water-separating inlet was 77 percent, which is considerably less than attainable with a … more
Date: June 8, 1948
Creator: von Glahn, Uwe
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ice protection of turbojet engines by inertia separation of water 3: annular submerged inlets

Description: Aerodynamic and icing studies were conducted on a one-half-scale model of an annular submerged inlet for use with axial-flow turbojet engines. Pressure recoveries, screen radial-velocity profiles, circumferential mass-flow variations, and icing characteristics were determined at the compressor inlet. In order to be effective in maintaining water-free induction air, the inlet gap must be extremely small and ram-pressure recoveries consequently are low, the highest achieved being 65 percent at in… more
Date: June 8, 1948
Creator: von Glahn, Uwe
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Initial Flight Test of the NACA FR-1-A, a Low-Acceleration Rocket-Propelled Vehicle for Transonic Flutter Research

Description: Report presenting testing on the first of a series of flutter rockets, designated the NACA FR-1-A, which was tested with two identical swept wings. Results regarding the launching, flight, and wing failure are provided.
Date: June 29, 1948
Creator: Angle, Ellwyn E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Internal-Film Cooling of Rocket Nozzles

Description: Experiments were conducted with 1000-pound-thrust rocket engine to determine feasibility of cooling convergent-divergent nozzle by internal film of water introduced at nozzle entrance. Water flow of 3 percent of propellant flow reduced heat flow into nozzle to 55 percent of uncooled heat flow. Introduction of water by porous ring before nozzle resulted in more uniform coverage of nozzle than water introduced by single arrangement of 36 jets directed along nozzle wall. Water flow through porous … more
Date: June 8, 1948
Creator: Sloop, J. L. & Kinney, George R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at supersonic speed (M = 1.53) of the pressure distribution over a 63 degrees swept airfoil of biconvex section at zero lift

Description: Report presenting an investigation of the distribution of pressure at zero lift over the surface of a swept airfoil of biconvex section. The measured pressures are compare with theoretical values calculated from thin-airfoil theory. Results regarding pressure distributions, drag, and boundary-layer studies are provided.
Date: June 10, 1948
Creator: Frick, Charles W. & Boyd, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 1: Characteristics of a Plain Wing

Description: Memorandum presenting wind-tunnel tests of a semispan model of an unswept wing of aspect ratio 4 and taper ratio 0.5 at Mach numbers up to 0.94 to determine its aerodynamic characteristics as influenced by Mach number, Reynolds number, and modification of the basic diamond profile by rounding the ridge. Lift, drag, and pitching-moment data are presented for a range of Reynolds and Mach numbers. The results indicated that no severe static-longitudinal-stability problems up to Mach number 0.94.
Date: June 2, 1948
Creator: Johnson, Ben H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Effects of Several Fuel-Injection Locations on Operational Performance of a 20-Inch Ram Jet

Description: Report presenting the results of an investigation to determine the effects of several methods of fuel injection on the operational performance of a 20-inch ram jet. Four fuel-injection arrangements using the same flame holder were presented. Results regarding the variation of combustion efficiency, ram-pressure ratio, location of the point of fuel injection, and range of fuel-air ratios over which combustion can be maintained are provided.
Date: June 8, 1948
Creator: Sterbentz, W. H.; Perchonok, E. & Wilcox, F. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An investigation of submerged air inlets on a 1/4-scale model of a typical fighter-type airplane

Description: Report presenting wind-tunnel testing of submerged air inlets on the fuselage of a scale model of a typical fighter-type airplane. The results are presented for ramp plan forms with parallel and with diverging walls and show the effect of the duct-entrance location, internal ducting efficiency, and deflectors.
Date: June 2, 1948
Creator: Delany, Noel K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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