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Longitudinal stability characteristics in maneuvering flight of the Convair XF-92A delta-wing airplane including the effects of wing fences

Description: Report presenting the longitudinal stability characteristics of the Convair XF-92A delta-wing airplane in maneuvering flight. The investigation included the determination of the characteristics of the basic airplane and the effects of two wing fence configurations on the characteristics.
Date: January 13, 1955
Creator: Sisk, Thomas R. & Muhleman, Duane O.
Item Type: Refine your search to only Report
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Experimental Investigation at High Subsonic Speeds of the Rolling Stability Derivatives of a Complete Model with an Aspect-Ratio-2.52 Wing Having an Unswept 72-Percent-Chord Line and a High Horizontal tail

Description: Memorandum presenting rolling stability derivatives for a complete model with a low-aspect-ratio wing and tail surfaces for a Mach number range of 0.70 to 0.94 and for an angle-of-attack range from 0 to 13 degrees for the lower Mach numbers. The model test results indicated regions of neutral or unstable damping in roll at Mach numbers of 0.85 and 0.90 in the higher angle-of-attack range for the basic model. Results regarding damping in roll, yawing moment and lateral force due to rolling, and … more
Date: May 26, 1955
Creator: Sleeman, William C., Jr. & Wiggins, James W.
Item Type: Refine your search to only Report
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Flight measurements of the dynamical longitudinal stability and frequency-response characteristics of the XF-92A delta-wing airplane

Description: Report presenting dynamic longitudinal maneuvers over a range of Mach numbers at an altitude of 30,000 feet by utilizing the XF-92A delta-wing research airplane. An analysis of the dynamic responses was made with three approaches: measured period and time to damp, analogue computer simulation of the airplane time-response characteristics, and Fourier transformation. Results regarding period, time and cycles to damp, and stability derivatives with Mach number are provided.
Date: January 13, 1955
Creator: Holleman, Euclid C. & Triplett, William C.
Item Type: Refine your search to only Report
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Flight Measurements of Elevon Hinge Moments on the XF-92A Delta-Wing Airplane

Description: Report presenting flight measurements of the elevon hinge moments on the Convair XF-92A delta-wing airplane over a range of Mach numbers during longitudinal elevon pulses, aileron rolls, and wind-up turns. During wind-up turns, the hinge moments become nonlinear at about the angle of attack at which the airplane experiences a marked decrease in longitudinal stability.
Date: January 13, 1955
Creator: Johnson, Clinton T. & Kuhl, Albert E.
Item Type: Refine your search to only Report
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Some Results of Flight Testing of Ski-Equipped Aircraft at the Naval Air Test Center

Description: Memorandum presenting the results of flight testing of four different ski-equipped airplanes. Two types of skis were tested: hydro-skis designed to operate under or on the water surface and general-purpose skis designed to operate on a variety of surfaces but not underwater. A breakdown of the ski performance for each plane and ski combination is provided.
Date: February 4, 1955
Creator: Beck, Preston E.
Item Type: Refine your search to only Report
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Effect of Inlet Temperature on Rotating Stall and Blade Vibrations in a Multistage Axial-Flow Compressor

Description: Report presenting rotating-stall and blade-vibration data for the first three rotor blade rows of a 13-stage axial-flow compressor at several inlet temperatures. Stall patterns of 1 through 5 stall zones were detected at all inlet temperatures in the equivalent compressor speed ranges between 4600 and 6200 rpm.
Date: August 5, 1955
Creator: Medeiros, Arthur A.; Calvert, Howard F. & Fenn, David B.
Item Type: Refine your search to only Report
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Some Effects of Configuration Variables on Store Loads at Supersonic Speeds

Description: Report presenting an analysis and examination of a large volume of data from several recent stores-research programs. For a given wing plan form, store position and configuration of angle of attack have been shown to be the most important parameters in the evaluation of store side force.
Date: July 6, 1955
Creator: Smith, Norman F. & Carlson, Harry W.
Item Type: Refine your search to only Report
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Effectiveness of a turbojet tubular combustor in screening the turbine from foreign objects

Description: Report presenting the effectiveness of a tubular combustor in screening the turbine from foreign objects measured with air flow corresponding to that at static sea-level rated operation. On average, the effectiveness of the production combustor was only 36 percent for the foreign objects introduced in the tests; that is, 64 percent of the objects penetrated the combustor. Results for six different configurations are provided.
Date: July 18, 1955
Creator: Chiarito, Patrick T.
Item Type: Refine your search to only Report
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Investigation of the Effects of Bomb-Bay Configuration Upon the Aerodynamic Characteristics of a Body With Circular Cross Section at Supersonic Speeds

Description: Memorandum presenting an investigation in the 9-inch supersonic tunnel to ascertain the lift, drag, and pitching moment associated with typical body-bomb-bay combinations with and without the bomb. Measurements were made at a range of angles of attack, Mach numbers, and Reynolds numbers.
Date: August 18, 1955
Creator: Rainey, Robert W.
Item Type: Refine your search to only Report
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Stability and control characteristics obtained during demonstration of the Douglas X-3 research airplane

Description: Report presenting flight tests performed using the Douglas X-3 research airplane during the manufacturer's demonstration program and U.S. Air Force evaluation. Tests were performed over a range of Mach numbers and altitudes. Longitudinal, lateral, and directional stability and control data were obtained during steady and maneuvering flight and are compared with wind-tunnel and rocket-model data in this report.
Date: July 21, 1955
Creator: Day, Richard E. & Fischel, Jack
Item Type: Refine your search to only Report
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Preparation and physical properties of some trialkylboranes

Description: Report presenting the preparation and properties of triethylborane, tri-n-propylborane, and tri-n-butylborane from boron triflouride and the appropriate Grignard reagent. Some of the characteristics examined included the freezing point, heat of fusion, boiling point, heat of combustion, refractive index, density, dielectric constant, and infrared spectra.
Date: November 1, 1955
Creator: Rosenblum, Louis & Allen, Harrison, Jr.
Item Type: Refine your search to only Report
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An Investigation of Jet Effects on Adjacent Surfaces

Description: "The steady pressure loads as well as the temperature change on adjacent surfaces due to the presence of a propulsive jet at subsonic speeds is shown to be insignificant. Whereas at supersonic speeds the temperature effect might be expected to remain insignificant, the steady pressure loads were shown to increase greatly on surfaces downstream of the propulsive jet exit" (p. 1).
Date: June 28, 1955
Creator: Bressette, Walter E. & Faget, Maxime A.
Item Type: Refine your search to only Report
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Performance of a Tubular Turbojet Combustor at High Pressures and Temperatures

Description: Memorandum presenting the effects on combustor performance of operation at the high inlet-air pressures, temperatures, and velocities representative of conditions that may be encountered in high-pressure-ratio turbojet engines or at high flight speeds studied in a single tubular combustor. Some of the performance characteristics investigated were combustor-liner temperatures, carbon deposition, smoke formation, and combustion efficiency.
Date: April 5, 1955
Creator: Butze, Helmut F. & Wear, Jerrold D.
Item Type: Refine your search to only Report
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Experimental performance of fluorine-oxygen with JP4 fuel in a rocket engine

Description: Report presenting the performance increase resulting from the addition of fluorine to the oxygen-JP4 rocket propellant combination evaluated experimentally in a 1000-pound-thrust engine with 0, 30, and 70 percent of fluorine by weight in the oxidant. Maximum specific impulse values obtained were 259, 278, and 287 pound-seconds per pound, respectively, at a combustion pressure of 600 pounds per square inch absolute.
Date: July 7, 1955
Creator: Douglass, Howard W.
Item Type: Refine your search to only Report
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Flight and Preflight Tests of a Ram Jet Burning Magnesium Slurry Fuel and Utilizing a Solid-Propellant Gas Generator for Fuel Expulsion

Description: Data obtained from the first flight test of a ram jet utilizing a magnesium slurry fuel are presented. The ram jet accelerated from a Mach number of 1.75 to a Mach number of 3.48 in 15.5 seconds. During this period a maximum values of air specific impulse and gross thrust coefficient were calculated to be 151 seconds and 0.658, respectively. The rocket gas generator used as a fuel-pumping system operated successfully.
Date: April 6, 1955
Creator: Bartlett, Walter A., Jr. & Hagginbothom, William K., Jr.
Item Type: Refine your search to only Report
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Preliminary Results of an Investigation at Transonic Speeds to Determine the Effects of a Heated Propulsive Jet on the Drag Characteristics of a Related Series of Afterbodies

Description: Preliminary results are presented from an investigation to determine the influence of afterbody geometry on the effects of a sonic propulsive jet at transonic speeds. The results presented are base pressure coefficient and afterbody pressure-drag coefficient as a function of jet pressure ratio for different values of Mach number and jet temperature. Geometric parameters investigated include boattail angle, jet-to-model diameter ratio, and jet-to-base diameter ratio.
Date: March 25, 1955
Creator: Henry, Beverly Z., Jr. & Cahn, Maurice S.
Item Type: Refine your search to only Report
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Experimental investigation of a transonic axial-flow-compressor rotor with double-circular-arc airfoil blade sections 3: comparison of blade-element performance with three levels of solidity

Description: Report presenting testing of two low-solidity transonic axial-flow-compressor rotors tested over a range of speeds up to a corrected tip speed of 1000 feet per second to determine the performance of such rotors and to provide experimental rotor blade-element data for low solidity levels. Comparisons of the hub and mean blade-element losses for the three rotors showed that the losses tended to decrease with a decrease in solidity. Results regarding rotor-inlet conditions, rotor-outlet conditions… more
Date: July 25, 1955
Creator: Schwenk, Francis C. & Lewis, George W., Jr.
Item Type: Refine your search to only Report
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Investigation at supersonic speeds of external-drag effects and pumping characteristics of a short ejector

Description: Report presenting an investigation at free-stream Mach numbers of 1.62, 1.94, and 2.41 to determine the external-drag effects and pumping characteristics of a short ejector housed within a highly bottailed afterbody. The tests covered secondary to primary diameter ratios of 1.50 and 1.33, mass flow ratios from 0 to 0.20, and a sonic and a supersonic primary nozzle. Results regarding drag and pumping characteristics are provided.
Date: June 14, 1955
Creator: Love, Eugene S. & O'Donnell, Robert M.
Item Type: Refine your search to only Report
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Experimental rocket performance with 15 percent fluorine - 85 percent oxygen and JP4

Description: From Summary: "Experimental performance of a rocket engine using 15 percent fluorine-85 percent oxygen and JP-4 was compared with that obtained using oxygen and JP-4. The regeneratively cooled engine was operated at 5000 pounds thrust and a chamber pressure of 350 pounds per square inch absolute. The peak specific impulse from 15 percent fluorine was 251 pound-seconds per pound. This is an increase of 3.3 percent over the 243 pound-seconds per pound obtained with fluorine."
Date: August 29, 1955
Creator: Tomazic, William A. & Rothenberg, Edward A.
Item Type: Refine your search to only Report
open access

Tests in the Ames 40- by 80-Foot Wind Tunnel of the Aerodynamic Characteristics of Airplane Models With Plain Spoiler Ailerons

Description: Memorandum presenting four wings of different plan forms equipped with plain spoiler ailerons tested at low speeds. Three of the models had wings of aspect ratio 3 and different taper ratios and sweep of the quarter-chord lines, while the fourth had an aspect ratio of 4.8, a taper ratio of 0.51, and sweep of 35 degrees.
Date: December 6, 1954
Creator: Franks, Ralph W.
Item Type: Refine your search to only Report
open access

Effect of yaw and angle of attack on pressure recovery and mass-flow characteristics of a rectangular supersonic scoop inlet at a Mach number of 2.71

Description: Report presenting an investigation of the effect of yaw and angle of attack on the total-pressure recovery and mass-flow characteristics of a rectangular supersonic scoop inlet designed to have low external drag at a Mach number of 2.7 and an angle of attack of 0 degrees. Total-pressure recovery and mass-flow data are presented for a Mach number of 2.71 at angles of yaw 0, 2.5, and 5 degrees and angles of attack of 0 and 5 degrees are provided.
Date: September 14, 1954
Creator: Comenzo, Raymond J. & Mackley, Ernest A.
Item Type: Refine your search to only Report
open access

Some Measurements of Boiling Burn-Out

Description: Report presenting measurements of boiling burn-out heat flux for water flowing upward through an electrically heated tube for ranges of velocity, pressure, length-diameter ratios, and subcooling.
Date: February 23, 1955
Creator: Lowdermilk, Warren H. & Weiland, Walter F.
Item Type: Refine your search to only Report
open access

Tests in the Ames 40- by 80-foot wind tunnel of the aerodynamic characteristics of airplane models with plain spoiler ailerons

Description: Report presenting four wings of different plan form equipped with plain spoiler ailerons tested at low speeds. Three of the models had wings of aspect ratio 3 and a range of taper ratios and sweep. The fourth model had aspect ratio 4.8 with taper ratio 0.51 and 35 degrees of sweep.
Date: December 6, 1954
Creator: Franks, Ralph W.
Item Type: Refine your search to only Report
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