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Flight Performance of a Twin-Engine Supersonic Ram Jet From 2,300 to 67,200 Feet Altitude

Description: Report presenting a flight investigation of a ground-launched supersonic twin ram-jet test vehicle using short flame-length burners. Results were obtained for a range of Mach numbers, altitudes, and fuel-air-ratios. Engine performance, gross thrust, fuel rate, total impulse, values of combustion efficiency and impulse, and overall combustion efficiency are also included.
Date: February 19, 1951
Creator: Dettwyler, H. Rudolph & Bond, Aleck C.
Partner: UNT Libraries Government Documents Department

Lift, Drag, and Pitching Moment of Low-Aspect-Ratio Wings at Subsonic and Supersonic Speeds: Triangular Wing of Aspect Ratio 2 with NACA 0005-63 Thickness Distribution, Cambered and Twisted for a Trapezoidal Span Load Distribution

Description: A wing-body combination having a plane triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution in streamwise planes, and twisted and cambered for a trapezoidal span load distribution has been investigated at both subsonic and supersonic Mach numbers. The lift, drag, and pitching moment of the model are presented for Mach numbers from 0.60 to 0.90 and 1.30 to 1.70 at a Reynolds number of 3.0 million. The variations of the characteristics with Reynolds number are also shown for several Mach numbers.
Date: February 5, 1951
Creator: Smith, Willard G. & Phelps, E. Ray
Partner: UNT Libraries Government Documents Department

Preliminary Transient Performance Data for Afterburner Operation of Westinghouse Electronic Power Regulator on XJ34-WE-32 Turbojet Engine in Altitude Wind Tunnel

Description: "At the request of the Bureau of Aeronautics, Department of the Navy, an investigation of the Westinghouse XJ34-WE-32 turbojet engine is being conducted in the NACA Lewis altitude wind tunnel to determine the steady-state and transient operating characteristics of the controlled and uncontrolled engine at various altitudes and ram pressure ratios. As part of this program, transient performance data that illustrate the operation of the engine is obtained in the form of oscillographic traces. Similar data for engine operation in the afterburning range, covering a range of throttle settings from the minimum value giving rated speed (throttle position, 72 degrees) to full afterburning (throttle position, 110 degrees), is presented herein" (p. 1).
Date: February 14, 1951
Creator: Vasu, George; Schwent, Glennon V. & Ketchum, James R.
Partner: UNT Libraries Government Documents Department

Factors Affecting the Starting Characteristics of Gas-Turbine Engines

Description: "This report summarizes the effects of fuel volatility and engine design variables on the problem of starting gas-turbine engines at sea-level and altitude conditions. The starting operation for engines with tubular combustors is considered as three steps; namely, (1) ignition of a fuel-air mixture in the combustor, (2) propagation of flame through cross-fire tubes to all combustors, and (3) acceleration of the engine from windmilling or starting speed to the operating speed range. Pertinent data from laboratory researches, single-combustor studies, and full-scale engine investigations are presented on each phase of the starting problem" (p. 1).
Date: February 8, 1951
Creator: Lewis Laboratory Fuels Panel
Partner: UNT Libraries Government Documents Department

Low-Speed Investigation of a Semisubmerged Air Scoop With and Without Boundary-Layer Suction

Description: "A preliminary low-speed investigation has been made of an air scoop submerged one-half the inlet height in a depression on the surface of a simulated fuselage. Boundary-layer suction was used on the steep approach ramp to improve the internal flow. A 6-degree-included-angle diffuser with an area ratio of 1.9:1 was located behind the inlet in the model. Most of the tests were conducted with an initial turbulent boundary layer believed to approximate that which would occur on the forward part of a fuselage" (p. 1).
Date: February 23, 1951
Creator: Pierpont, P. Kenneth & Howell, Robert R.
Partner: UNT Libraries Government Documents Department

Supersonic Tunnel Investigation by Means of Inclined-Plate Technique to Determine Performance of Several Nose Inlets Over Mach Number Range of 1.72 to 2.18

Description: Memorandum presenting a study using a suspended flat plate to continuously vary the Mach number in the 18- by 18-inch Mach number 1.91 supersonic tunnel. The technique was applied to the determination of pressure recovery and mass-flow characteristics of four supersonic nose inlets over the Mach number range produced. Results regarding the plate calibration and inlet performance are provided.
Date: February 14, 1951
Creator: Fox, Jerome L.
Partner: UNT Libraries Government Documents Department

Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 3: conical-spike all-external-compression inlet with supersonic cowl lip

Description: Memorandum presenting an investigation conducted in the Lewis 8- by 6-foot supersonic wind tunnel to determine the force and pressure characteristics of an all-external compression inlet with a conical spike and a supersonic cowl lip. Measurements of lift, drag, pitching moment, and internal and external pressures were made at free-stream Mach numbers of 1.59, 1.79, and 1.99 for a range of mass-flow ratios and angles of attack to 10 degrees.
Date: February 14, 1951
Creator: Weinstein, Maynard I. & Davids, Joseph
Partner: UNT Libraries Government Documents Department

Dynamic stability and control characteristics of a vertically rising airplane model in hovering flight

Description: Report presenting an investigation to determine the stability and control characteristics of a vertically rising airplane model. Results of preliminary hovering flight tests are made in still air, away from the interference effects of the ground and side walls, and with normal airplane-type controls operating in the slipstream.
Date: February 23, 1951
Creator: Bates, William R.; Lovell, Powell M., Jr. & Smith, Charles C., Jr.
Partner: UNT Libraries Government Documents Department

An investigation of the spray characteristics of a jet-powered dynamic model of the drag flying boat with a vee tail : TED No. NACA DE 328

Description: An investigation was made of the spray characteristics of a jet-powered dynamic model of the Bureau of Aeronautics DR 56 flying-boat design with a vee tail. A limited investigation was made to determine the effect of the change in tail design on the take-off and landing behavior in smooth water and in waves 8 feet high (full size).
Date: February 28, 1951
Creator: Carter, Arthur W.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics at transonic speeds of a 69 degree delta wing with a triangular plan-form control having a skewed hinge axis and an overhang balance: transonic-bump method

Description: From Introduction: "Presented in this paper are the results of an investigation of a semispan model of a delta wing with 60^o sweepback at the leading edge which was equipped with a large triangular control having an overhang balance mounted on a skewed hinge axis. The purpose of this investigation was to determine the aerodynamic characteristics of a delta wing with a control which was designed to provide aerodynamic balance at zero control deflection based on the span load distribution of reference 1."
Date: February 6, 1951
Creator: Wiley, Harleth G.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: triangular wing of aspect ratio 4 with NACA 0005-63 thickness distribution, cambered and twisted for trapezoidal span load distribution

Description: "A wing-body combination having a triangular wing of aspect ratio 4 with NACA 0005-63 thickness distribution in streamwise planes, and cambered and twisted for a trapezoidal span distribution has been investigated at both subsonic and supersonic Mach numbers. The lift, drag, and pitching moment of the model are presented for Mach numbers from 0.25 to 0.96 and 1.20 to 1.70 at a Reynolds number of 1.5 million. The variations of the characteristics with Reynolds number are also shown for several Mach numbers" (p. 1).
Date: February 2, 1951
Creator: Phelps, E. Ray & Smith, Willard G.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution, cambered and twisted for a trapezoidal span load distribution

Description: Report presenting a wing-body combination with a plane triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution in streamwise planes, which has been twisted and cambered for a trapezoidal span load distribution at subsonic and supersonic Mach numbers.
Date: February 5, 1951
Creator: Smith, Willard G. & Phelps, E. Ray
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 2 with NACA 0008-63 section

Description: Report presenting an investigation of a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0008-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: February 1, 1951
Creator: Smith, Donald W. & Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

Description: From Introduction: "The wings were tested in combination with fuselage similar to the one used in the 7- by 10-foot wind-tunnel investigations. The results are reported herein and are compared with results for three similar model wings on the transonic bump (references 1, 2, and 3)."
Date: February 6, 1951
Creator: Sutton, Fred B. & Martin, Andrew
Partner: UNT Libraries Government Documents Department

Free-flight performance of 16-inch diameter supersonic ram-jet units 4: performance of ram-jet units designed for combustion chamber inlet Mach number of 0.21 at free-stream Mach number of 1.6 over a range flight conditions

Description: Report presenting an investigation of 16-inch-diameter ram-jet units under free-flight conditions to determine performance at high subsonic, transonic, and supersonic velocities. Full-scale units were released from the airplane at high altitudes and accelerated by the engine thrust and force of gravity. Results regarding the diffuser total-pressure recovery, drag, thrust coefficient, and combustion are provided.
Date: February 26, 1951
Creator: Rabb, Leonard & North, Warren J.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 4 with NACA 0005-63 section

Description: Report presenting an investigation of a wing-body combination with a plane triangular wing of aspect ratio 4 and NACA 0005-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: February 2, 1951
Creator: Heitmeyer, John C. & Stephenson, Jack D.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 2 with NACA 0005-63 section

Description: Report presenting a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0005-63 sections in streamwise planes has been investigated at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: February 1, 1951
Creator: Smith, Donald W. & Heitmeyer, John C.
Partner: UNT Libraries Government Documents Department

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 2 with NACA 0003-63 section

Description: Report presenting testing of a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0003-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: February 2, 1951
Creator: Heitmeyer, John C. & Smith, Willard G.
Partner: UNT Libraries Government Documents Department

Preliminary flight investigation of the maneuvering accelerations and buffet boundary of a 35 degree swept-wing airplane at high altitude and transonic speeds

Description: Report presenting the results of a series of exploratory flights on a 35 degree swept-wing airplane up to Mach number 1.09 to show the effects of compressibility on imposing maneuverability limits. Results regarding the maneuvering accelerations and buffet boundary are provided.
Date: February 21, 1951
Creator: Rathert, George A., Jr.; Ziff, Howard L. & Cooper, George E.
Partner: UNT Libraries Government Documents Department

Altitude-test-chamber investigation of performance of a 28-inch ram-jet engine 3: combustion and operational performance of three flame holders with a center pilot burner

Description: Report presenting a direct-connect altitude test chamber investigation of the combustion performance of a 28-inch-diameter ramjet engine with a can-type center pilot burner. Combustion-chamber configurations with three different flame holders were investigated at a simulated flight Mach number of 2.0 and several different altitudes.
Date: February 6, 1951
Creator: Shillito, Thomas B.; Younger, George G. & Henzel, James G., Jr.
Partner: UNT Libraries Government Documents Department

An investigation of convergent-divergent diffusers at Mach number 1.85

Description: Report presenting an investigation in the supersonic tunnel at Mach number 1.85 and angles of attack from 0 to 5 degrees to determine optimum design configurations for a convergent-divergent type of supersonic diffusers with a subsonic diffuser of 5 degrees included divergence angle. Total-pressure recoveries in excess of the theoretical recovery across a normal shock at a free-stream Mach number of 1.85 were obtained with a number of configurations.
Date: February 2, 1951
Creator: Wyatt, DeMarquis D. & Hunczak, Henry R.
Partner: UNT Libraries Government Documents Department

The effects of centrally mounted wing-tip tanks on the subsonic aerodynamic characteristics of a wing of aspect ratio 10 with 35 degrees of sweepback

Description: Report presenting an investigation of the effects of three centrally mounted wing-tip tanks on the aerodynamic characteristics of a cambered wing with an aspect ratio of 10 and 35 degrees of sweepback. Testing occurred over a range of Mach and Reynolds numbers and lift, drag, and pitching-moment were measured.
Date: February 21, 1951
Creator: Tinling, Bruce E. & Kolk, W. Richard
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept, tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps - leading-edge flaps deflected

Description: Report presenting aerodynamic characteristics of an unswept wing with an aspect ratio of 2.67, a taper ratio of 0.5, and employing full-span, 25-percent chord, plain, leading-edge flaps using wind-tunnel testing of a semispan model. The leading edge flap was generally effective at changing both the lift and pitching-moment coefficients at each angle of attack and Mach number. Results regarding lift characteristics, hinge-moment characteristics, drag characteristics, and pitching-moment characteristics are provided.
Date: February 26, 1951
Creator: Stivers, Louis S., Jr. & Malick, Alexander W.
Partner: UNT Libraries Government Documents Department

The effects of Mach number and Reynolds number on the aerodynamic characteristics of several 12-percent-thick wings having 35 degrees of sweepback and various amounts of camber

Description: Report presenting a comparison of the lift, drag, and pitching-moment characteristics of several wings with 35 degrees of sweepback and various amounts of camber in wind-tunnel testing. Six semispan model wings were tested, three with an aspect ratio of 10 and three with an aspect ratio of 5. Results regarding model distortion under aerodynamic loads, effects of Reynolds number, effects of Mach number, and effects of camber are provided.
Date: February 23, 1951
Creator: Tinling, Bruce E. & Kolk, W. Richard
Partner: UNT Libraries Government Documents Department