National Advisory Committee for Aeronautics (NACA) - 158 Matching Results

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Experimental investigation of flow fields at zero sideslip near swept- and unswept-wing-fuselage combinations at low speed

Description: Report presenting an experimental determination of the flow fields near swept- and unswept-wing-fuselage combinations at zero sideslip as determined experimentally at low speed for various spanwise and vertical locations and angles of attack as variations with chordwise distance. Results regarding the swept-wing-fuselage flow fields, unswept-wing-fuselage flow fields, and a comparison of wing-fuselage and fuselage-alone flow fields are provided.
Date: January 18, 1957
Creator: Alford, William J., Jr. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some Dielectric Properties of Suspensions of Boron Powders in Mineral Oil

Description: Memorandum presenting measurements of the dielectric constant for suspensions of two types of boron powder in mineral oil as a function of concentration of boron particles, moisture content, temperature, and frequency of oscillation. Also investigated were the effects of boron-powder concentration and moisture content on the dielectric losses of mineral-oil suspensions of the two boron powders.
Date: August 18, 1955
Creator: Altshuller, Aubrey P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A flight investigation of the effect of leading-edge camber on the aerodynamic characteristics of a swept-wing airplane

Description: Report presenting flight measurements on a swept-wing jet aircraft to determine the effects of adding forward camber and an increased leading-edge radius on the low-speed stalling characteristics, the high-speed static longitudinal stability, and the airplane drag. The modified leading edge produced values of maximum lift somewhat greater than the slats on a normal airplane, but the stall was unacceptable because of an abrupt roll-off.
Date: February 18, 1953
Creator: Anderson, Seth B.; Matteson, Frederick H. & Van Dyke, Rudolph D., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measured Data Pertaining to Buffeting at Supersonic Speeds of the Douglas D-558-II Research Airplane

Description: Report presenting data obtained from an investigation of the Douglas-D558-II airplane to determine its buffeting characteristics at high lift and supersonic speeds. From Summary: "Buffeting was encountered at normal-force coefficients greater than about 0.7 in the Mach number range from 0.96 to 1.27 but at Mach number of 1.57, a peak normal-force coefficient of 0.80 was attained with no indication of buffeting. The increase in buffet intensity with lift is very gradual at supersonic speed compa… more
Date: February 18, 1954
Creator: Baker, Thomas F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Stability and control characteristics of a 1/4-scale Bell X-5 airplane model in the landing configuration

Description: Report presenting an investigation of the static stability and control characteristics of a scale model of a preliminary Bell X-5 airplane design in the landing configuration with and without dive brakes. Results regarding the effects of slats, flaps, landing gear, gear doors, dive brakes and gap at the wing root are provided.
Date: December 18, 1950
Creator: Becht, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Evaluation of Centrifugal Compressor Performance With Water Injection

Description: The effects of water injection on a compressor are presented. To determine the effects of varying water-air ratio, the compressor was operated at a constant equivalent impeller speed over a range of water-air ratios and weight flows. Operation over a range of weight flows at one water-air ratio and two inlet air temperatures was carried out to obtain an indication of the effects of varying inlet air temperature. Beyond a water-air ratio of 0.03 there was no increase in maximum air-weight flow, … more
Date: July 18, 1951
Creator: Beede, William L.; Hamrick, Joseph T. & Withee, Joseph R., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Thrust and drag characteristics of simulated variable-shroud nozzles with hot and cold primary flows at subsonic and supersonic speeds

Description: Report presenting an experimental investigation of a series of fixed-geometry exhaust nozzles which simulated a variable exit, which was conducted in the 8- by 6-foot supersonic wind tunnel at Mach numbers 0, 0.6, 1.5, 1.7, and 2.0. Gross thrust performance of the long-shroud exit configurations was considerably better than the short-shroud. Results regarding flow coefficients, thrust characteristics, flight performance analysis of data, and shroud drag are provided.
Date: February 18, 1955
Creator: Beke, Andrew & Simon, Paul C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of additives on pressure limits of flame propagation of propane-air mixtures

Description: Report presenting a study of seven additives in 0.5-volume-percent concentration for their effects on the low-pressure limits of flame propagation of propane-air mixtures. Limits were measured in a flame tube of new design. Results regarding propane-air mixtures, propane-air-additive mixtures, and flame propagation qualities are provided.
Date: December 18, 1953
Creator: Belles, Frank E. & Simon, Dorothy M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Spinning-Tunnel Investigation of a 1/30-Scale Model of the Grumman XF10F-1 Airplane

Description: "An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/30 - scale model of the Grumman XFlOF-1 airplane to determine its spin and recovery characteristics. The investigation included erect and inverted spins for both the straight-wing and swept-wing configurations. Tests to determine the optimum size spin-recovery parachutes and the rudder forces required for recovery were also made" (p. 1).
Date: December 18, 1950
Creator: Berman, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of wing flexibility on the damping roll of a notched delta-wing body combination between Mach numbers 0.6 and approximately 2.2 as determined with rocket-propelled models

Description: Report presenting an investigation with sting-mounted rocket-propelled models in free flight at approximately zero lift to determine the effect of wing flexibility on the damping-in-roll characteristics of a wing-body combination over a range of Mach numbers.
Date: June 18, 1954
Creator: Bland, William M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some Effects of Heat Transfer at Mach Number 2.0 at Stagnation Temperatures Between 2,310 and 3,500 Degrees R on a Magnesium Fin With Several Leading-Edge Modifications

Description: Report presenting testing of four models of a thin magnesium fin, with the leading edge swept back 35 degrees, of a type used to stabilize the first stages of rocket-propelled multistage hypersonic models. The investigation was carried out to determine some effects of aerodynamic heating at high stagnation temperatures on the leading edges of fins and to determine the relative effectiveness of several leading-edge protective methods. The fins tested included a basic fin, a fin with a blunt lead… more
Date: April 18, 1957
Creator: Bland, William M., Jr. & Bressette, Walter E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Performance Data on General Electric Integrated Electronic Control Operating on J47 RX1-3 Turbojet Engine in NACA Altitude Wind Tunnel

Description: From Summary: "Performance data obtained with recording oscillographs are presented to show the transient response of the General Electric Integrated Electronic Control operating on the J47 RXl-3 turbo-Jet engine over a range of altitudes from 10,000 to 45,000 feet and at ram pressure ratios of 1.03 and 1.4. These data represent the performance of the final control configuration developed after an investigation of the engine transient behavior in the NACA altitude wind tunnel. Oscillograph trac… more
Date: July 18, 1950
Creator: Blivas, Darnold & Taylor, Burt L., III
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation in the Langley Free-Flight Tunnel of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model Simulating the Convair F-102A Airplane

Description: "An investigation of the low-speed, power-off stability and control characteristics of a 1/10-scale model simulating the Convair F-102A airplane has been made in the Langley free-flight tunnel. The model in its basic configuration and with two modifications involving leading- edge slats and an increase in vertical-tail size was flown through a lift-coefficient range from 0.7 to the stall. Only relatively low-altitude conditions were simulated" (p. 1).
Date: February 18, 1955
Creator: Boisseau, Peter C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Forces and Pressure Distribution at Subsonic Speeds on a Cambered and Twisted Wing Having 45 Degrees of Sweepback and Aspect Ratio of 3 and a Taper Ratio of 0.5

Description: Memorandum presenting an investigation conducted to determine the effects of scale and compressibility on the forces, moments, and pressure distribution on a cambered and twisted wing with an aspect ratio of 3.0 and a taper ratio of 0.5. Lift, drag, and pitching-moment data and the chordwise distribution of static pressure at seven spanwise stations are presented for specified Mach and Reynolds numbers. In order to determine the effects of camber and twist, the force, moment, and pressure data … more
Date: July 18, 1952
Creator: Boltz, Frederick W. & Kolbe, Carl D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A comparison of the experimental and theoretical loading over triangular wings in sideslip at supersonic speeds

Description: The results of an experimental investigation of the load distribution over two triangular wings in sideslip at Mach numbers from 1.20 to 1.79 are presented and compared with theory. The two wings tested have identical plan form, 45 degrees sweepback of the leading edge, and an aspect ratio of 4.0. One model was composed of round-nose airfoil sections and the other of sharp-nose, biconvex sections. For both wings the maximum thickness of streamwise sections was 6 percent and was located at the 3… more
Date: May 18, 1951
Creator: Boyd, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A study of conical camber for triangular and sweptback wings

Description: Report presenting a theoretical and experimental study to determine the effectiveness of camber in reducing the drag due to lift resulting from pressure forces acting on low-aspect-ratio triangular and sweptback wings. Design charts are included which aid in the selection of camber for various sweepback angles and Mach numbers. Results regarding drag characteristics and lift and moment characteristics are provided.
Date: November 18, 1955
Creator: Boyd, John W.; Migotsky, Eugene & Wetzel, Benton E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Behavior of Pentaborane-Air Combustion Products During Expansion in a Convergent Divergent Nozzle

Description: "In order to evaluate the post combustion behavior of boric oxide, pentaborane-air mixtures, burned to completion at a combustor pressure of 3 atmospheres, were expanded through a 7.1-inch-long convergent-divergent nozzle having a 4-inch-diameter throat and an exit-to-throat area ratio of 1.68. The experimentally determined thrust performance was in good agreement with the ideal equilibrium performance at stagnation temperatures of 3300 deg R and lower. The boric oxide vapor at the combustor ex… more
Date: February 18, 1958
Creator: Branstetter, J. Robert & Setze, Paul C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental behavior of pentaborane-air combustion products during expansion in a convergent-divergent nozzle

Description: Report presenting an evaluation of the postcombustion behavior of boric oxide using pentaborane-air mixtures burned to completion at a combustor pressure of 3 atmospheres expanded through a convergent-divergent nozzle. Results regarding the symmetry of flow in nozzle, behavior of liquid boric oxide in nozzle, abrupt condensation phenomena, effect of abrupt condensation on performance, and effect of oxide films are provided.
Date: February 18, 1958
Creator: Branstetter, J. Robert & Setze, Paul C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Ground Tests of the Elevator Power Control System and Feel Device in a Boeing B-47A Airplane

Description: Memorandum presenting ground tests made on the longitudinal control system in a Boeing B-47A airplane. The simulator tests showed the pilot-airplane-control-system combination to be satisfactory in spite of the relatively large phase lags noticed in the frequency-response tests. Results regarding the relation between elevator angle and stick force, relation between stick angle and stick force, relation between elevator angle and stick angle, and the simulator tests are provided.
Date: October 18, 1954
Creator: Brown, B. Porter
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Heat Transfer and Boundary-Layer Transition on a Highly Polished Hemisphere-Cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 10(Exp 6)

Description: "A highly polished hemisphere-cone having a ratio of nose radius to base radius of 0.74 and a half-angle of 14.5 degrees was flight tested at Mach numbers up to 4.70. Temperature and pressure data were obtained at Mach numbers up to 3.14 and a free-stream Reynolds number of 24 x 10(exp 6) based on body diameter. The nose of the model had a surface roughness of 2 to 5 microinches as measured with an interferometer" (p. 1).
Date: April 18, 1957
Creator: Buglia, James J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Note on the Scavenge of 6-Inch-Diameter Ram-Jet Exhaust in Mach 3.1, 1- by 1-Foot Supersonic Tunnel

Description: From Summary: "The exhaust of a 6-inch-diameter ram-jet engine mounted in the Lewis 1- by 1-foot, Mach 3.1 supersonic tunnel was scavenged successfully with a 6.6-inch-diameter scoop. Limiting values of exhaust-to-stream static-pressure ratios and scavenge-system total-pressure ratios were determined for complete scavenging of the products of combustion. The scavenge-system operation influenced the engine exhaust-nozzle pressures under conditions of unstable scavenge flow."
Date: February 18, 1955
Creator: Burgess, Warren C., Jr. & Baughman, L. Eugene
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Blade Failures in a J34, Eleven-Stage Axial-Flow Compressor

Description: Report presenting a vibrational survey conducted during normal operation of a production eleven-stage axial-flow compressor powered as part of a complete turbojet engine. After serious third-stage vibration was detected, an investigation was conducted to study and eliminate the vibration with several component configurations. The vibrational source was determined to be an aerodynamic phenomenon related to a stall, but a new inlet-guide-vane assembly with a 4-percent increase in inlet area elimi… more
Date: May 18, 1953
Creator: Calvert, Howard F.; Meyer, André J., Jr. & Morse, C. Robert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a Model of a 40.4 Degree Swept-Wing Airplane at Mach Numbers of 1.56 and 2.06

Description: Memorandum presenting an investigation to determine the drag, longitudinal stability, and lateral stability characteristics of a model of a fighter-type airplane. Several modifications were made to the model in an attempt to eliminate pitch-up.
Date: January 18, 1957
Creator: Carmel, Melvin M. & Turner, Kenneth L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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