Technical Report Archive & Image Library (TRAIL) - 31 Matching Results

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The aerodynamic characteristics throughout the subsonic speed range of a thin, sharp-edged horizontal tail of aspect ratio 4 equipped with a constant-chord elevator

Description: From Introduction: "Recent investigations have indicated several wing plan forms, wing sections, and wing-body-tail combinations suitable for flight at supersonic speeds. One such lifting surface, a thin, sharp-edged without sweep of aspect ratio 4 and taper ratio 0.5, has been the subject of an investigation in the Ames 12-foot pressure wind tunnel. The aim of the investigation was to determine the aerodynamic characteristics of such a wing plan form throughout the range of subsonic Mach numbe… more
Date: June 30, 1949
Creator: Bandettini, Angelo & Reed, Verlin D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Application of an ultraviolet spectrophotometric method to the estimation of alkylnaphthalenes in 10 experimental jet-propulsion fuels

Description: Report presenting the combustion efficiencies of 10 experimental jet-propulsion fuels that are approximately 200 degrees Fahrenheit cuts of five selected crudes available in large quantities in a turbojet engine combustor at altitude conditions.
Date: April 30, 1947
Creator: Cleaves, Alden P. & Carver, Mildred S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Buffeting of External Fuel Tanks at High Speeds on a Grumman F7F-3 Airplane

Description: Attempts were made to alleviate the buffeting of external fuel tanks mounted under the wings of a twin-engine Navy fighter plane. The Mach number at which the buffeting began was increased from 0.529 to 0.640 by streamlining the sway braces and increasing the lateral rigidity of the sway brace system. Further increases of the Mach number, at which buffeting began to 0.725, was obtained by moving the external fuel tank to a position under the fuselage.
Date: January 30, 1947
Creator: Turner, Howard L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of High-Lift Devices on the Low-Speed Static Lateral and Yawing Stability Characteristics of an Untapered 45 Degrees Sweptback Wing

Description: Memorandum presenting a wind-tunnel investigation made in the stability tunnel to determine the effects of lift flaps on the static lateral stability derivatives and the yawing derivatives of an untapered 45 degree sweptback wing at low speeds. Results regarding straight flow and yawing characteristics are provided.
Date: September 30, 1948
Creator: Lichtenstein, Jacob H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Slot-Entry Skirt Extensions on Aerodynamic Characteristics of a Wing Section of the XB-36 Airplane Equipped with a Double Slotted Flap

Description: "An investigation was made in the Langley two-dimensional low-turbulence tunnel on a wing section for the XB-36 airplane equipped with a double slotted flap to determine the effect on lift and drag of various slot-entry skirt extension. A skirt extension of 0.787 deg. was found to provide the best combination of high maximum lift with flap deflected and law drag with flap retracted. The data showed that the maximum lift at intermediate (20 deg. to 45 deg.) flap deflections was lowered considera… more
Date: June 30, 1947
Creator: Cahill, Jones F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Compressibility on the Flow Past Thick Airfoil Sections

Description: "Six, 3-inch-chord symmetrical airfoil sections having systematic variations in thickness and thickness location were tested at Mach numbers near flight values for propeller-shank sections. The tests, the results of which are presented in the form of schlieren photographs of the flow past each model and pressure-distribution charts for two of the model, were performed to illustrate the effects of compressibility on the flow past thick symmetrical airfoil sections. Representative flow photograph… more
Date: January 30, 1947
Creator: Daley, Bernard N. & Humphreys, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms: August 23, 1946 to September 4, 1946 at Orlando, Florida

Description: This report presents the results obtained from gust and draft velocity measurements within thunderstorms for the period August 23, 1946 to September 4, 1946 at Orlando, Florida. These data are summarized in tables I end II and are of the type presented in reference 1 for previous flights. In several of the surveys, indications of ambient air temperature were obtained from photo-observer records. These data are summarized in table III.
Date: January 30, 1946
Creator: Tolefson, H. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of performance and operating characteristics of a tail-pipe burner for a turbojet engine

Description: Report presenting an investigation to obtain fundamental information required for the design of a satisfactory tail-pipe burner for augmenting turbojet engine thrust. Investigations were also conducted to determine the combustion and pressure-drop characteristics of the most satisfactory burner, to develop a method of controlling the burner-outlet temperature distribution, and to improve the burner ignition characteristics.
Date: October 30, 1947
Creator: Gabriel, David S.; Martinson, E. Vincent & Essig, Robert H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigations at High-Subsonic, Transonic, and Supersonic Speeds to Determine Zero-Lift Drag of Fin-Stabilized Bodies of Revolution having Fineness Ratios of 12.5, 8.91, and 6.04 and Varying Positions of Maximum Diameter

Description: Rocket-powered models were flown at high-subsonic, transonic, and supersonic speeds to determine the zero-lift drag of fin-stabilized parabolic bodies of revolution differing in fineness ratio and in position of maximum diameter. The present paper presents the results for fineness ratio 12.5, 8.91 and 6.04 bodies having maximum diameters located at stations of 20, 40, 60, and 80 percent of body length. All configurations had cut-off sterns and all had equal base, frontal, and exposed fin areas.… more
Date: November 30, 1949
Creator: Hart, Roger G. & Katz, Ellis R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning-Tunnel Tests of a 1/18-Scale Model of the Fairchild XNQ-1 Airplane, TED No. NACA 2398

Description: :Spin tests have been performed in the Langley 20-foot free-spinning tunnel on a 1/18-scale model of the Fairchild XNQ-1 airplane. The spin and recovery characteristics of the model were determined for the normal gross-weight loading and for two variations from this loading - center of gravity moved rearward and relative mass distribution increased along the fuselage. These tests were performed for two vertical-tail plan forms. The investigation also included simulated pilot-escape tests and ru… more
Date: September 30, 1946
Creator: Daughtridge, Lee T., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Full-Scale Investigation of an Equilateral Triangular Wing Having 10-Percent-Thick Biconvex Airfoil Sections

Description: Report discussing an investigation of the low-speed characteristics of a wing with a triangular plan form, 60 degrees of sweepback at the leading edge, and 10-percent-thick biconvex airfoil sections. The purpose of the investigation was to determine the effects of semispan and full-span leading-edge and trailing-edge flaps on the longitudinal aerodynamic characteristics of the wing and the effects of a vertical fin on the lateral stability characteristics.
Date: September 30, 1948
Creator: Whittle, Edward F., Jr. & Lovell, J. Calvin
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

Investigation of Performance of Single-Stage Axial-Flow Compressor Using NACA 5509-34 Blade Section

Description: Memorandum presenting an investigation conducted to study the performance of a single-stage axial-flow compressor using blades with an NACA 5509-34 airfoil section. Static- and total-pressure, total-temperature, and flow-angle surveys were taken in the compressor inlet and outlet and between blade rows to study the overall performance and individual blade-row performance.
Date: September 30, 1948
Creator: Mankuta, Harry & Guentert, Donald C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Langley full-scale tunnel investigation of the characteristics in yaw of a trapezoidal wing of aspect ratio 4 with circular-arc airfoil sections

Description: Report presenting an investigation to determine the characteristics in yaw of a trapezoidal wing of aspect ratio 4 with circular-arc airfoil sections and 0.20-chord rear and drooped-nose flaps. Measurements of lift, lateral force, rolling moment, and yawing moment of four configurations were made for a range of angles of attack and yaw angles.
Date: August 30, 1948
Creator: May, Ralph W., Jr. & Stevens, George L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Control Characteristics at Transonic Speeds of a Semispan Airplane Model Having a 45 Degree Sweptback Wing and Tail as Obtained by the Transonic-Bump Method

Description: Report presenting a wind-tunnel investigation using the transonic-bump method to determine the longitudinal stability and control characteristics of a semispan airplane model with a 45 degree sweptback wing and tail at transonic speeds. An increase in the rate of change of the pitching-moment coefficient with lift coefficient at a constant Mach number through the transonic range was noted.
Date: June 30, 1948
Creator: Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance investigation of can-type combustor 2: water injection at various stations in combustor

Description: Report presenting an investigation to determine the maximum quantity of water that could be injected either into or ahead of a single can-type combustor without reducing the attainable combustor-outlet temperature below the value required for engine operation and without the appearance of liquid water at the combustor outlet. Water was injected from spray nozzles at four different stations along the combustor.
Date: September 30, 1948
Creator: Cook, William P. & Zettle, Eugene V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Axial-Flow Supersonic Compressor on XJ-55-FF-1 Turbojet Engine 1: Preliminary Performance of Compressor

Description: An investigation was conducted to determine the performance characteristics of the axial-flow supersonic compressor of the XJ-55-FF-1 turbo Jet engine. The test unit consisted of a row of inlet guide vanes and a supersonic rotor; the stator vanes after the rotor were omitted. The maximum pressure ratio produced in the single stage was 2.28 at an equivalent tip speed or 1814 feet per second with an adiabatic efficiency of approximately 0.61, equivalent weight flow of 13.4 pounds per second. The … more
Date: January 30, 1949
Creator: Hartmann, Melvin J. & Graham, Robert C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of J-33-A-21 Turbojet-Engine Compressor I - Over-All Performance Characteristics at Equivalent Impeller Speeds from 6000 to 13,400 RPM

Description: "The NACA is investigating a series of J-33 turbojet-engine compressors to determine the over-all and component performances and to improve theories of flow through large centrifugal compressors, The production model J-33-A-21 was operated over a range of inlet temperatures from 80 to -40 F and inlet pressures from 14 to 5 inches mercury absolute for equivalent impeller speeds from 6000 to 13,400 rpm. At the equivalent design speed of 11,500 rpm, the compressor had a peak pressure ratio of 3.98… more
Date: March 30, 1948
Creator: Beede, William L.; Kovach, Karl & Creagh, John W. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of the 19XB 10-Stage Axial-Flow Compressor

Description: The 19xB compressor, which replaces the 19B compressor and has the same length and diameter 88 the 19B compressor, was designed with 10 stages to deliver 30 pounds of air per second for a pressure ratio of 4.17 at an equivalent speed of 17,000 rpm; the 19B was designed with six stages for a pressure ratio of 2.7 at the same weight flow and speed as the 19XB compressor. The performance characteristics of the new compressor were determined at the NACA Cleveland laboratory at the request of the Bu… more
Date: December 30, 1946
Creator: Downing, Richard M. & Finger, Harold B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Tests of a Buffet Stall-Warning Device on a 1/5-Scale Model of the Republic XP-84 Airplane

Description: "During the first flight tests of the Republic XP-84 airplane it was discovered that there was a complete lack of stall warning. A short series of development tests of a suitable stall-warning device for the airplane was therefore made on a 1/5-scale model in the Langley 300 MPH 7- by 10-foot tunnel. Two similar stall-warning devices, each designed to produce early root stall which would provide a buffet warning, were tested" (p. 1).
Date: October 30, 1946
Creator: Tucker, Warren A. & Comisarow, Paul
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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