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NACA Conference on High-Speed Aerodynamics: A Compilation of Papers Presented

Description: A reproduction of the technical papers presented by staff members of the NACA Laboratories at the NACA Conference on High-Speed Aerodynamics at the Ames Aeronautical Laboratory during March 18-20, 1958. The primary purpose of the conference was to convey to military services and contractors the results of recent research and to provide an opportunity to discuss the results.
Date: 1958-03-18/1958-03-20
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a 1/60-Scale Model of the Republic MX-1554 Airplane at a Mach Number of 2.85

Description: Report presenting the results of an investigation to determine the static longitudinal and lateral stability and control characteristics of a model of the Republic MX-1554 airplane at a specified Mach and Reynolds number. No analysis was provided in the paper in order to expedite publication.
Date: March 18, 1953
Creator: Dickey, Robert R. & Spahr, J. Richard
Item Type: Refine your search to only Report
open access

Experimental Investigation of a Body Flare for Obtaining Pitch Stability and a Body Flap for Obtaining Pitch Control in Hypersonic Flight

Description: Memorandum presenting the effectiveness of a body flare as a pitch-stabilizing device and a body flap as a pitch-control device investigated experimentally at Mach numbers from 3.00 to 6.25. The basic test body was rotationally symmetric and consisted of a fineness ratio 3 nose followed by a fineness ratio 9 afterbody. Results regarding the stability of the flared body, effect of body flap on lift and drag, trim conditions, flow visualization studies, and comparison of theory and experiment are… more
Date: January 18, 1955
Creator: Eggers, A. J., Jr. & Syvertson, Clarence A.
Item Type: Refine your search to only Report
open access

Development of a Supersonic Area Rule and an Application to the Design of a Wing-Body Combination Having High Lift-to-Drag Ratios

Description: Report presenting a concept for interrelating the wave drag of wing-body combinations at moderate supersonic speeds with axial distributions of cross-sectional area has been developed. Details of preliminary experiments meant to test the concept are also provided.
Date: August 18, 1953
Creator: Whitcomb, Richard T. & Fischetti, Thomas L.
Item Type: Refine your search to only Report
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
open access

Boundary-Layer-Transition and Heat-Transfer Measurements from Flight Tests of Blunt and Sharp 50 Degree Cones at Mach Numbers from 1.7 to 4.7

Description: Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt and sharp cones having apex angles of 50 deg. The test Mach number range was from 1.7 to 4.7, corresponding to free-stream Reynolds numbers, based on cone base diameter, of 18. 3 x 10(exp 6) and 32.1 x 10(exp 6), respectively. Transition on both models occurred at a local Reynolds number of 1 x 10(exp 6) to 2 X 10(exp 6) based on distance from the stagnation point. Transition Reynolds numbers base… more
Date: April 18, 1957
Creator: Chauvin, Leo T. & Speegle, Katherine C.
Item Type: Refine your search to only Report
open access

Adaptation of a Cascade Impactor to Flight Measurement of Droplet Size in Clouds

Description: "A cascade impactor, an instrument for obtaining the size distribution of droplets borne in a low-velocity air stream, was adapted for flight cloud droplet-size studies. The air containing the droplets was slowed down from flight speed by a diffuser to the inlet-air velocity of the impactor" (p. 1).
Date: September 18, 1951
Creator: Levine, Joseph & Kleinknecht, Kenneth S.
Item Type: Refine your search to only Report
open access

Boundary-Layer Measurements on Several Porous Materials With Suction Applied

Description: Memorandum presenting the boundary-layer velocity profiles were measured on ten samples of various porous materials and on impervious aluminum plate mounted flush with the inner surface of the side wall of a small wind tunnel. Suction was applied to the back side of the porous test materials through a 4-inch-square opening. Results regarding measurements on the impervious plate and measurements on porous materials without suction and with suction are provided.
Date: June 18, 1952
Creator: McCullough, George B. & Gambucci, Bruno J.
Item Type: Refine your search to only Report
open access

Spark Ignition of Flowing Gases. 2: Effect of Electrode Parameters on Energy Required to Ignite a Propane-Air Mixture

Description: From Summary: "Research was conducted to determine the effect of the electrode parameters of spacing, configuration, and material' on the energy required for ignition of a flowing propane-air mixture. In addition, the data were used to indicate the energy distribution along the spark length and to confirm previous observations concerning the effect of spark duration on ignition energy requirements. The data were obtained with a mixture at a fuel-air ratio of 0.0835 (by weight), a pressure of 3 … more
Date: December 18, 1951
Creator: Swett, Clyde C., Jr.
Item Type: Refine your search to only Report
open access

Investigation of Two Bluff Shapes in Axial Free Flight Over a Mach Number Range From 0.35 to 2.15

Description: Report presenting testing of a fineness-ratio-2.71 right circular cylinder and a fineness-ratio-4.0 circular cylinder with a rounded nose and flared afterbody over a range of Mach and Reynolds numbers. Time histories, cross plots of force coefficients, rolling velocity, and longitudinal-force coefficient are provided for the two cylinders.
Date: March 18, 1958
Creator: Coltrane, Lucille C.
Item Type: Refine your search to only Report
open access

Investigation of a 0.6 Hub-Tip Radius-Ratio Transonic Turbine Designed for Secondary-Flow Study 2 - Design and Experimental Performance of Turbine With Low-Velocity-Turning Stator and Standard Rotor

Description: Memorandum presenting a low-velocity-turning stator designed to reduce secondary-flow loss cores by turning the flow at low velocities and accelerating it in passages of constant flow angle with reduced cross-channel pressure gradients. Performance of the stator was determined with static-pressure measurements and detailed surveys of total pressure and flow angle made with the turbine operating at design speed near design work.
Date: July 18, 1957
Creator: Rohlik, Harold E.; Wintucky, William T. & Scibbe, Herbert W.
Item Type: Refine your search to only Report
open access

An Investigation of the Effects of Nose and Lip Shapes for an Underslung Scoop Inlet at Mach Numbers from 0 to 1.9

Description: An experimental investigation was conducted to determine the performance characteristics an underslung nose-scoop air-induction system for a supersonic airplane. Five different nose shapes, three lip shapes, and two internal diffusers were investigated. Tests were made at Mach numbers from 0 to 1.9, angles of attack from 0 deg to approximately l5 deg, and mass-flow ratios from 0 to maximum obtainable. It was found that the underslung nose-scoop inlet was able to operate at Mach numbers from 0.6… more
Date: November 18, 1955
Creator: Pfyl, Frank A.
Item Type: Refine your search to only Report
open access

Some Design and Operational Considerations of a Liquid-Hydrogen Fuel and Heat-Sink System for Turbojet-Engine Tests

Description: Memorandum presenting an experimental investigation in which liquid hydrogen was used as a heat sink for turbine-cooling in a high-temperature turbojet engine. Several problems were revealed which will require special attention in future work. The primary issue was pressure surging in the fuel system, which presented a problem in flow measurement and control.
Date: December 18, 1956
Creator: Corrington, Lester C.; Thornbury, Kenneth L. & Hennings, Glen
Item Type: Refine your search to only Report
open access

Drag Measurements at Low Lift of a Four-Nacelle Airplane Configuration Having a Longitudinal Distribution of Cross-Sectional Area Conductive to Low Transonic Drag Rise

Description: Memorandum presenting a procedure based on the transonic area rule, which has been used to design a four-nacelle delta-wing airplane configuration. A flight test of a model of the configuration showed a zero-lift transonic drag rise of 0.010 which, when compared with estimates, indicated the absence of adverse interference effects.
Date: November 18, 1953
Creator: Hopko, Russell N.; Piland, Robert O. & Hall, James R.
Item Type: Refine your search to only Report
open access

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
open access

Lateral-control investigation of flap-type and spoiler-type controls on a wing with quarter-chord-line sweepback of 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Description: Report presenting an investigation by the transonic-bump method through a range of Mach numbers in the high speed 7- by 10-foot tunnel to determine the lateral-control characteristics of a semispan wing-fuselage combination equipped with flap-type and spoiler-type controls. Both the flap-type and spoiler-type controls provide lateral control through the Mach number range investigated.
Date: July 18, 1950
Creator: Hammond, Alexander D.
Item Type: Refine your search to only Report
open access

The transonic characteristics of a low-aspect-ratio triangular wing with a constant-chord flap as determined by wing-flow tests, including correlation with large-scale tests

Description: Report presenting wing-flow-method measurements for 0.47 to 1.15 Mach number of the longitudinal-stability and -control characteristics of a triangular wing of aspect ratio 2 equipped with a constant-chord flap. Changes in the lift-curve slope and aerodynamic-center position through the transonic speed range were moderate and gradual. Results regarding triangular-wing characteristics, flap characteristics, and a comparison of the wind-tunnel and free-flight-test results at higher Reynolds numbe… more
Date: August 18, 1950
Creator: Rathert, George A., Jr.; Rolls, L. Stewart & Hanson, Carl M.
Item Type: Refine your search to only Report
open access

Pressure Distributions on the Blade Sections of the NACA 10-(5)(066)-03 Propeller Under Operating Conditions

Description: A report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for eight radial stations of the NACA 10-(5)(066)-03 propeller.
Date: April 18, 1950
Creator: Evans, Albert J. & Luchuk, Wallace
Item Type: Refine your search to only Report
open access

Pressure Distributions on the Blade Sections of the NACA 10-(0)(066)-03 Propeller Under Operating Conditions

Description: The fifth report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(0)(066)-03 propeller.
Date: May 18, 1950
Creator: Steinberg, Seymour & Milling, Robert W.
Item Type: Refine your search to only Report
open access

Investigation of effect of span and spanwise location of plain and stepped spoiler ailerons on lateral control characteristics of a wing with leading edge swept back 51.3 degrees

Description: Report presenting a wind-tunnel investigation at low speed to determine the lateral control characteristics of a 51.3 degree sweptback-wing model equipped with either plain or stepped spoiler ailerons with a fixed projection of 5-percent-wing chord and various spans and spanwise locations. The results indicated that spanwise rolling-effectiveness charts of flap-type ailerons can not be used to predict effectiveness of spoiler-type ailerons on swept wings. Results regarding the wing aerodynamic … more
Date: January 18, 1950
Creator: Fischel, Jack & Hammond, Alexander D.
Item Type: Refine your search to only Report
open access

Ditching Tests With a 1/16-Size Model of the Navy XP2V-1 Airplane at the Langley Tank No. 2 Monorail

Description: Report discussing tests using a model of the Navy XP2V-1 to study its performance when ditched. From Summary: "Various landing attitudes, speeds, and conditions of damage were simulated. The performance of the model was determined and recorded from visual observations, by recording time histories of the longitudinal decelerations, and by taking motion pictures of the ditchings."
Date: May 18, 1950
Creator: Fisher, Lloyd J. & Tarshis, Robert P.
Item Type: Refine your search to only Report
open access

Analytical investigation of flow and heat transfer in coolant passages of free-convection liquid-cooled turbines

Description: From Introduction: "An analytical investigation of the problems arising in connection with this cooling method was conducted at the NACA Lewis laboratory and is presented herein. This analysis investigates: (1) the smallest diameter hole that can be made without endangering the circulation of the liquid, and (2) methods of improving the circulation in a small-diameter hole."
Date: July 18, 1950
Creator: Eckert, E. R. G. & Jackson, Thomas W.
Item Type: Refine your search to only Report
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