National Advisory Committee for Aeronautics (NACA) - 155 Matching Results

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Performance Characteristics of Several Divergent-Shroud Aircraft Ejectors

Description: Report presenting an investigation of ten divergent- and two cylindrical-shroud ejectors to determine internal ejector performance over a range of pressure ratios and expansion area ratios for Mach numbers up to about 3. Results regarding jet-thrust and air-handling characteristics and net-thrust performance are provided.
Date: September 8, 1955
Creator: Greathouse, William K. & Beale, William T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 6. - Swept-Wing Heavy-Bomber Configuration With Stores of Different Sizes and Shapes

Description: Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference performed in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a heavy-bomber airplane with stores of several shapes and sizes.
Date: March 8, 1956
Creator: Smith, Norman F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Results of the Flight Test of a 0.13-Scale Rocket-Boosted Model of the McDonnell F4H-1 Airplane Between Mach Numbers of 0.20 and 1.90

Description: Report discussing tests performed with a rocket-boosted model of the McDonnell F4H-1 airplane at transonic and supersonic speeds. Special attention is given to the external drag coefficient at various Mach numbers. Large pitching oscillations were also noted at Mach numbers between 0.20 and 1.17, which made it impossible to determine the drag at that range.
Date: November 8, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Investigation at High Subsonic Speeds of Drag at 0 Degrees Angle of Attack of Swept-Wing Fuselage Models With Pylon Mounted and Semisubmerged Missiles

Description: Report discussing testing on two wing-fuselage models with 45 degree sweptback wings and various missile arrangements, one with pylons underneath the wing and one with the missiles semisubmerged in the sides of the fuselage. A comparison of the drag of both types of models was made.
Date: October 8, 1956
Creator: King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Synthesis and Hydrolysis-Rate Studies of Decaborane Derivatives

Description: Report discussing a series of experiments involving the reaction of water with decaborane and HEF-3, a boron fuel containing ethyldecaborane. The chemical properties of the hydrolysis reaction are described. Two isomers were also prepared to assist with the syntheses, and their melting points, molecular weights, and solubilities in certain solvents are included.
Date: October 8, 1957
Creator: Lucas, D. & Lipschitz, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Drag and Lateral-Stability Characteristics of a 1/22-Scale Model of a Bomber Airplane Employing a Low-Aspect-Ratio Triangular Wing

Description: Report presenting the results of an investigation of cross-sectional-area distribution, nacelle configuration, and landing-gear-fairing configuration on the minimum drag characteristics of a model of a four-engine bomber airplane with a low-aspect-ratio triangular wing. The lateral stability characteristics are also included.
Date: July 8, 1953
Creator: Phelps, E. Ray
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of an All-Movable Control Surface at a Mach Number of 6.86 for Possible Flutter

Description: Memorandum presenting results of tests for possible flutter of a dynamically and elastically scaled model of a proposed all-movable horizontal tail surface for the North American X-15 airplane. Tests at Mach number 6.86 were made on the scaled model and on several other configurations with lower stiffnesses.
Date: May 8, 1958
Creator: Lauten, William T., Jr.; Levey, Gilbert M. & Armstrong, William O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of Dynamic Lateral Stability Characteristics of a Configuration of the North American X-15 Research Airplane

Description: Memorandum presenting an investigation to determine the dynamic lateral stability characteristics of a configuration of the North American X-15 research airplane. Of specific concern were characteristic modes, period and damping, airplane response to yaw and roll controls, ratio of roll to sideslip in the Dutch-roll oscillation, and the roll-coupling problem. Results regarding stability-boundary plots, characteristic roots, roll-to-sideslip ratio, and time histories are provided.
Date: February 8, 1957
Creator: Moul, Martin T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tabulated Pressure Data for a Series of Controls on a 40 Degree Sweptback Wing at Mach Numbers of 1.61 and 2.01

Description: "An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers of 1.7 x l0(exp 6) and 3.6 x l0(exp 6) to determine the pressure distributions over a swept wing with a series of 14 control configurations. The wing had 40 deg of sweep of the quarter-chord line, an aspect ratio of 3.1, and a taper ratio of 0.4. Measurements were made at angles of attack from 0 deg to +/- 15 deg for control deflections from -60 deg to 60 deg. This report contains tabulated pressure data for t… more
Date: November 8, 1957
Creator: Lord, Douglas R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Comparison of Flight-Measured Carrier- Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations

Description: Memorandum presenting lift and drag characteristics that have been determined in flight in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements, including various wing boundary-layer-control installations. Minimum comfortable approach speeds for carrier-type landings were evaluated for these airplanes by four test pilots. Results regarding the presentation of data, methods for the prediction of minimum comfortable approach speed, reasons for limiting approac… more
Date: May 8, 1958
Creator: White, Maurice D.; Schlaff, Bernard A. & Drinkwater, Fred J., III
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pumping Characteristics for Several Simulated Variablegeometry Ejectors With Hot and Cold Primary Flow

Description: Report presenting an investigation of the pumping characteristics of eight conical ejectors mounted on a scale fuselage portion of a supersonic airplane. The configurations simulated various positions of a two-position nozzle with a fixed shroud and double-iris exit. Results regarding ejector pumping characteristics, comparison with previous results, comparison of data for cold and hot primary flow, and ejector air-supply requirements are provided.
Date: September 8, 1954
Creator: Allen, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparative Drag Measurements at Transonic Speeds of 6-Percent-Thick Airfoils of Symmetrical Double-Wedge and Circular-Arc Sections From Tests by the NACA Wing-Flow Method

Description: Report presenting comparative drag measurements at zero lift at transonic speeds for two sharp-leading-edge airfoils using the NACA wing-flow method. One airfoil had a symmetrical circular-arc section and one had a symmetrical double-wedge section. The primary difference in the drag characteristics of the two airfoils at zero lift is the earlier drag rise of the double-wedge section.
Date: April 8, 1947
Creator: Silsby, Norman S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of the transonic drag characteristics of two wing-body combinations differing only in the location of the 45 degree sweptback wing

Description: Report presenting the drag of a series of wing-body combinations by the free-fall method in order to provide information on the drag characteristics of promising transonic and supersonic airplane arrangements. Time histories, Mach number variations, and drag coefficients for several areas of the body are provided.
Date: December 8, 1947
Creator: Mathews, Charles W. & Thompson, Jim Rogers
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and NACA 65A004 airfoil section: transonic-bump method

Description: From Introduction: "This paper presents the results of an investigation of force and moment characteristics for a wing with an unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and an NACA 65A004 airfoil section parallel to the free stream."
Date: March 8, 1950
Creator: Polhamus, Edward C. & Campbell, George S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A004 airfoil section: Transonic-bump method

Description: From Introduction: "This paper presents the results of the investigation of the wing alone and of the wing-fuselage configurations employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A004 airfoil section parallel to the air stream. The experimental results of a wing of identical plan from having an NACA 65A006 airfoil section which was tested as part of the transonic program are presented in reference 1.
Date: May 8, 1950
Creator: Myers, Boyd C., II & Wiggins, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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
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Notes on Geared Tabs at Supersonic Speeds

Description: Memorandum presenting an analysis of the two-dimensional, geared, trailing-edge flap-tab combination at supersonic speeds to determine if the combination could be used to reduce the hinge moments to extremely small values while retaining a large part of the lift effectiveness of a plain flap with the same ratio of flap chord to wing chord.
Date: July 8, 1948
Creator: Tucker, Warren A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag Measurements of a Swept-Back Wing Having Inverse Taper as Determined by Flight Tests at Supersonic Speeds

Description: Report discussing the results of flight tests to determine the drag at zero lift of a swept-back wing of inverse taper using an NACA 65-009 airfoil. The data was compared to untapered wings with a similar degree of sweepback. The tapered wing was found to have a lower drag coefficient than the 34-degree swept-back untapered wing but a higher drag coefficient than the 45-degree swept-back untapered wing.
Date: April 8, 1947
Creator: Alexander, Sidney R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation of thrust augmentation of axial-flow-type 4000-pound-thrust turbojet engine by water and alcohol injection at compressor inlet

Description: Report presenting an experimental investigation of thrust augmentation of an axial-flow-type turbojet engine with a 4000-pound-thrust rating using a water-alcohol injection at the compressor inlet at sea-level conditions and zero ram. Three injection systems were investigated in order to obtain satisfactory atomization and distribution of the injected liquids. Results regarding engine performance and engine operation are provided.
Date: July 8, 1948
Creator: Baron, Burnett; Dowman, Harry W. & Dackis, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Estimated transonic flying qualities of a tailless airplane based on a model investigation

Description: Report presenting an analysis of the estimated flying qualities of a tailless airplane with the wing quarter-chord line swept back 35 degrees in a range of Mach numbers based on tests of a model of the airplane in the 7- by 10-foot tunnel. Results regarding performance, longitudinal stability and control, and lateral stability and control are provided.
Date: June 8, 1949
Creator: Donlan, Charles J. & Kuhn, Richard E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Theoretical Investigation of the Dynamic Lateral Oscillatory Stability of an Airplane Having a 60 Degree Triangular Wing

Description: Report presenting a theoretical study of the dynamic lateral stability characteristics of an airplane with a 60 degree triangular wing. Calculations included the determination of the neutral-lateral-oscillatory-stability boundary, the period and time to damp to one-half amplitude of the lateral oscillation, and the time to damp to one-half amplitude for the spiral mode. The airplane was generally found to be stable for all conditions.
Date: March 8, 1950
Creator: Johnson, Joseph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Model ditching investigation of the Douglas DC-4 and DC-6 airplanes

Description: Report presenting the ditching characteristics of the Douglas DC-4 and DC-6 in a water tank. Dynamically similar models of 1/16 scale were used for the investigation, which was conducted in calm and rough water. The ditching characteristics and safest ditching procedures were determined by testing at various landing attitudes, speeds, and simulated conditions of damage.
Date: November 8, 1949
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Investigation of a Parabolic Body of Revolution at Mach Number of 1.92 and Some Effects of an Annular Jet Exhausting From the Base

Description: Report discussing an investigation of a parabolic body of revolution with and without the effects of an annular jet exhausting from the base. The aerodynamic characteristics, pressures, lift-curve slope, and other characteristics with the jet in operation and inoperative were compared.
Date: February 8, 1950
Creator: Love, Eugene S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Estimation of Range of Stability Derivatives for Current and Future Pilotless Aircraft

Description: Memorandum presenting an analysis made of the probable range of the stability parameters of present and future missiles. Included is a short review of the dynamic theory and some of the factors and assumptions influencing the stability derivatives and equations of motion.
Date: October 8, 1947
Creator: Pitkin, Marvin & Ankenbruck, Herman O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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