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open access

Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings

Description: Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are pr… more
Date: October 7, 1953
Creator: Radin, Edward J. & Carpenter, Paul J.
Item Type: Refine your search to only Report
open access

Flight measurements of directional stability to a Mach number of 1.48 for an airplane tested with three different vertical tail configurations

Description: Report presenting flight tests to measure the directional stability of a fighter-type airplane over a range of Mach numbers. Testing occurred at two altitudes and used three vertical tails of varying aspect ratio or area.
Date: October 7, 1955
Creator: Drake, Hubert M.; Finch, Thomas W. & Peele, James R.
Item Type: Refine your search to only Report
open access

A theoretical analysis of the effect of engine angular momentum on longitudinal and directional stability in steady rolling maneuvers

Description: From Summary: "The effect of engine momentum on the longitudinal and directional stability of aircraft in steady rolling maneuvers has been investigated. The results presented indicate that the gyroscopic moments produced on the aircraft by rotating engine in rolling maneuvers can have an appreciable effect on the range of rolling velocities for which longitudinal or directional instability might occur."
Date: October 7, 1955
Creator: Gates, Ordway B., Jr. & Woodling, C. H.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/10-Scale Model of the Douglas A4D-1 Airplane

Description: Report discussing an experimental investigation of the low-speed rolling stability derivatives of a model of the Douglas A4D-1. The model was tested under a variety of conditions, including in clean and landing configurations and with the horizontal and vertical tails on and off, and the study also explored the effects of slats and flaps on the derivatives of the wing. No analysis of the data is provided.
Date: October 7, 1954
Creator: Wolhart, Walter D. & Fletcher, H. S.
Item Type: Refine your search to only Report
open access

Flight Investigation of a Roll-Stabilized Ramjet Test Vehicle Over a Mach Number Range of 2.3 to 2.7

Description: Report presenting a flight investigation on a roll-stabilized ramjet test vehicle to determine engine performance over a range of Mach numbers, a range of fuel-air ratio, and an altitude range. Results regarding engine performance and roll autopilot performance are provided.
Date: October 7, 1955
Creator: Kennedy, Thomas L. & Trout, Otto F., Jr.
Item Type: Refine your search to only Report
open access

A comparison of the simulated-altitude performance of two turbojet combustor types

Description: Report presenting a comparison of the performance of a German Jumo 004 can-type combustor and the performance of two contemporary United States turbojet combustors to determine whether the Jumo 004 was more advanced and to determine whether there are basic, inherent differences in the performance achieved with the can or annular combustor type. Results regarding altitude operational limits, combustion efficiency, pressure loss, and temperature profile at combustor outlet are provided.
Date: October 7, 1948
Creator: Bolz, Ray E.; Schroeter, Thomas T. & Zettle, Eugene V.
Item Type: Refine your search to only Report
open access

Control Effectiveness Load and Hinge-Moment Characteristics of a Tip Control Surface on a Delta Wing at a Mach Number of 1.9

Description: Report presenting a wind-tunnel investigation of a semispan delta wing with the leading-edge swept back 60 degrees. A half-delta control surface was used and testing was performed with and without fences. Results regarding the rolling effectiveness, wing characteristics, and control-surface characteristics are provided.
Date: October 7, 1949
Creator: Conner, D. William & May, Ellery B., Jr.
Item Type: Refine your search to only Report
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Aerodynamic characteristics in sideslip of a large-scale model having a 63 degree swept-back vertical tail

Description: Report presenting an investigation to determine the effects of a vertical tail with the leading edge swept back 63 degrees on the aerodynamic characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees. The aerodynamic characteristics in sideslip with and without the vertical tail are also presented. Results regarding the directional stability, rudder effectiveness, and rudder hinge moments are described.
Date: October 7, 1949
Creator: McCormack, Gerald M.
Item Type: Refine your search to only Report
open access

Ditching tests of a 1/15-scale model of the Fairchild C-82 airplane

Description: Given here are results of tests made in calm water at various landing attitudes, speeds, and simulated conditions of damage. It was concluded that the best ditching could be made by contacting the water as near the stall angle as possible without losing adequate control. The landing flaps should be full down. If the paratainer hatch and aft-cargo doors fail as expected in a ditching, there will be a large inrush of water into the cargo compartment which makes this location a very hazardous ditc… more
Date: October 7, 1948
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
Item Type: Refine your search to only Report
open access

A Preliminary Investigation of the Usefulness of Camber in Obtaining Favorable Airfoil-Section Drag Characteristics at Supercritical Speeds

Description: Report presenting an investigation to determine the possibility of delaying at moderate or large lift coefficients the onset of the abrupt supercritical drag rise of an airfoil section by the use of camber. Results indicated that the addition of camber to the NACA 0010 airfoil leads to significant improvements in the drag characteristics at moderately supercritical speeds .
Date: October 7, 1949
Creator: Nitzberg, Gerald E.; Crandall, Stewart M. & Polentz, Perry P.
Item Type: Refine your search to only Report
open access

Some Effects of Spoiler Height, Wing Flexibility, and Wing Thickness on Rolling Effectiveness and Drag of Unswept Wings at Mach Numbers Between 0.4 and 1.7

Description: Report presenting rolling effectiveness and drag tests of spoilers on unswept wings over a range of Mach numbers using rocket-propelled test vehicles in free flight. The wings tested had an aspect ratio of 3.7, were unswept and untapered, had thickness ratios of 3, 6, and 9 percent, and covered a range of flexibilities. Results regarding the rolling effectiveness and drag are provided.
Date: October 7, 1952
Creator: Fields, E. M.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of the Motion of a 1/10-Scale Model of the Douglas XF4D-1 Escape Capsule When Jettisoned by Jet Ejection: TED No. NACA DE 359

Description: Memorandum presenting a wind-tunnel investigation at low speed to determine the path and motion of a scale model of the Douglas XF4D-1 escape capsule without the drogue parachute when jettisoned by jet ejection. The investigation included determination of the vertical and horizontal accelerations of the capsule. Results regarding the ejection at zero airspeed, ejection at 570 feet per second, and at 863 feet per second are provided.
Date: October 7, 1953
Creator: Johnson, Harold S.
Item Type: Refine your search to only Report
open access

Investigation of Reynolds Number Effects for a Series of Cone-Cylinder Bodies at Mach Numbers of 1.62, 1.93, and 2.41

Description: "An investigation of the Reynolds number for transition and the skin-friction drag at zero lift of eight cone-cylinder bodies having various fineness ratios has been made at Mach numbers of 1.62, 1.93, and 2.41 over a Reynolds number range from 0.3 x 10(exp 6) to 10 x 10(exp 6). The accuracy of the skin-friction data was not sufficient to permit any general conclusions to be drawn. The Reynolds number for transition was found to be dependent upon both the tunnel stagnation pressure and Mach num… more
Date: October 7, 1953
Creator: Grigsby, Carl E. & Ogburn, Edmund L.
Item Type: Refine your search to only Report
open access

Investigation of the Effect of Spanwise Positioning of a Vertically Symmetric Ogive-Cylinder Nacelle on the High-Speed Aerodynamic Characteristics of a 45 Degree Sweptback Tapered-in-Thickness Wing of Aspect Ratio 6 With and Without a Fuselage

Description: Report presenting an investigation of an ogive-cylinder nacelle in various spanwise locations in a vertically symmetric position on a small-size 45 degree sweptback wing of aspect ratio 6 with and without a fuselage. Results regarding the drag characteristics, lift-drag ratios, lift characteristics, pitch characteristics, and lateral center of pressure are provided.
Date: October 7, 1953
Creator: Silvers, H. Norman & King, Thomas J., Jr.
Item Type: Refine your search to only Report
open access

Flight experience with a delta-wing airplane having violent lateral-longitudinal coupling in aileron rolls

Description: From Summary: "During a flight investigation of the lateral stability characteristics of a high-speed delta-wing airplane, violent cross-coupled lateral and longitudinal motions were encountered. The maneuver which produced these motions was an abrupt, rudder-fixed aileron roll performed at a Mach number of 0.75 at about 40,000 feet. The motions were characterized by extreme variations in angle of attack and angle of sideslip which caused the airplane to exceed the normal and transverse acceler… more
Date: October 7, 1955
Creator: Sisk, Thomas R. & Andrews, William H.
Item Type: Refine your search to only Report
open access

Flight Investigation of a Roll-Stabilized Ram-Jet Test Vehicle Over a Mach Number Range of 2.3 to 2.7

Description: Report presenting a flight investigation on a roll-stabilized ram-jet test vehicle over a range of Mach numbers from 2.3 to 2.7, a range of fuel-air ratio from 0.038 to 0.050, and an altitude range from 3,000 to 40,000 feet. Results regarding test conditions, engine performance, and roll autopilot performance are provided. The engines operated satisfactorily over the test time and the roll-control system operated satisfactorily at the beginning of testing.
Date: October 7, 1955
Creator: Kennedy, Thomas L. & Trout, Otto F., Jr.
Item Type: Refine your search to only Report
open access

Wind-tunnel investigation at low speed of the rolling stability derivatives of a 1/10-scale model of the Douglas A4D-1 airplane: TED No. NACA DE 389

Description: Report presenting an experimental investigation to determine the low-speed rolling stability derivatives of a scale model of the Douglas A4D-1. The model was tested in clean and landing configurations with horizontal and vertical tails on and off. The data is presented without analysis.
Date: October 7, 1954
Creator: Wolhart, Walter D. & Fletcher, H. S.
Item Type: Refine your search to only Report
open access

Transonic Flutter Investigation of a Fighter-Airplane Wing Model and Comparison With a Systematic Plan-Form Series

Description: Report presenting an investigation of the transonic flutter characteristics at zero lift of a model of a wing for a new fighter airplane. The characteristics were found to be similar to those of a comparable systematic plan-form series of models described in previous reports. Results regarding visual observations, damping, flutter-speed ratio, and ratio of experimental sustained flutter speeds to reference flutter speeds are provided.
Date: October 7, 1955
Creator: Land, Norman S. & Abbott, Frank T., Jr.
Item Type: Refine your search to only Report
open access

Preliminary Altitude Performance Data of J71-A2 Turbojet Engine Afterburner

Description: The performance and operational characteristics of the J71-A2 turbojet-engine afterburner were investigated for a range of altitudes from 23,000 to 60,000 feet at a flight Mach number of 0,9 and at flight Mach numbers of 0.6, 0.9, and 1.0 at an altitude of 45,000 feet. The combustion performance and altitude operational limits, as well as the altitude starting characteristics have been determined.
Date: October 7, 1954
Creator: Useller, James W. & Mallett, William E.
Item Type: Refine your search to only Report
open access

Flight Investigation of Effect of Various Vertical-Tail Modifications on the Directional Stability and Control Characteristics of the P-63A-1 Airplane (AAF No. 42-68889)

Description: "Because the results of preliminary flight tests had indicated the P-63A-1 airplane possessed insufficient directional stability, the NACA and the manufacturer (Bell Aircraft Corporation) suggested three vertical-tail modifications to remedy the deficiencies in the directional characteristics. These modifications included an enlarged vertical tail formed by adding a tip extension to the original vertical tail, a large sharp-edge ventral fin, and a small dorsal fin. The enlarged vertical tail in… more
Date: October 7, 1946
Creator: Johnson, Harold I.
Item Type: Refine your search to only Report
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