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Aileron and Elevator Hinge Moments of the Bell X-1 Airplane Measured in Transonic Flight

Description: "During the flight investigation of the X-1 airplane the hinge moments of the elevator and aileron control surfaces have been measured over a Mach number range extending to above 1.0. The results of these measurements are presented in this paper" (p. 2).
Date: June 22, 1953
Creator: Drake, Hubert M. & McKay, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-Speed Wind-Tunnel Tests of a 1/16-Scale Model of the D-558 Research Airplane Lift and Drag Characteristics of the D-558-1 and Various Wing and Tail Configurations

Description: "Tests were made in the Langley 8-foot high-speed tunnel to investigate the aerodynamic characteristics of the D-558-1 airplane and various wing and tail configurations on the D-558-1 fuselage. The various wing and tail configurations were tested to determine the aerodynamic effects of aspect ratio and sweep for suitable use on the second phase of the D-558 project (D-558-2). The tests were conducted through a speed range from a Mach number of 0.40 to approximately 0.94" (p. 1).
Date: 1953
Creator: Wright, John B. & Loving, Donald L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing loads on the Bell X-1 research airplane (10 percent thick wing) as determined by pressure-distribution measurements in flight at subsonic and transonic speeds

Description: Report presenting measurements of wing loads made on the left wing of the Bell X-1 research airplane. Data are presented within a wing-panel normal-force coefficient and Mach number range. Results regarding span load distributions, wing-panel aerodynamic characteristics, and wing-to-fuselage carry over are provided.
Date: November 4, 1953
Creator: Knapp, Ronald J. & Jordan, Gareth H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Description: An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the rolling stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller blade angle were investigated for the complete model. Most of the tests were made through an angle-of-attack range from … more
Date: May 20, 1953
Creator: Queijo, M. J.; Wolhart, Walter D. & Fletcher, H. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of fluctuating pressures on a 1/4-scale model of the X-1 airplane with a 10-percent-thick wing in the Langley 16-foot transonic tunnel

Description: Report presenting pressure fluctuations measured near the trailing edge of the wing and near the leading edge of the tail of a scale model of the X-1 airplane with a 10-percent-thick wing in the 16-foot transonic tunnel. Results regarding frequency analyses are also provided.
Date: January 7, 1953
Creator: Habel, Louis W. & Steinberg, Seymour
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements of Pressures on Base and Rear Part of Fuselage of the Bell X-1 Research Airplane at Transonic Speeds, Including Power Effects

Description: Report presenting measurements made on the Bell X-1 airplane to determine the pressures on the fuselage base and rear portion of the fuselage during level flight. Measurements were made in the power-off condition and with the engine operating. Information about the power-off pressures and jet effects is provided.
Date: January 28, 1953
Creator: Knapp, Ronald J. & Johnson, Wallace E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-speed static stability and control characteristics of a 1/4-scale model of the Bell X-1 airplane equipped with a 4-percent-thick, aspect-ratio-4, unswept wing

Description: Report presenting an investigation in the Langley 300 mph tunnel to determine the low-speed static stability and control characteristics of a model of the Bell X-1 airplane equipped with a 4-percent-thick, aspect-ratio-4 wing. Tests were also made to determine optimum flap deflection for a slotted flap. Results regarding longitudinal stability and control, high lift devices, lateral and directional stability, and lateral and directional control are provided.
Date: November 2, 1953
Creator: Moseley, William C., Jr. & Taylor, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight-Determined Pressure Distributions Over the Wing of the Bell X-1 Research Airplane (10-Percent-Thick Wing) at Subsonic and Transonic Speeds

Description: Report presenting measurements of chordwise pressure distributions at four spanwise stations over a 10-percent-thick wing of the Bell X-1 airplane. Results regarding pressure distributions at the various stations and section aerodynamic characteristics are presented. The data was obtained for a range of Mach numbers from 0.30 to 11.9 and altitudes from 17,000 to 47,000 with several different types of maneuvers.
Date: June 29, 1953
Creator: Knapp, Ronald J. & Jordan, Gareth H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of Lift and Drag for the Bell X-1 Research Airplane Having a 10-Percent-Thick Wing

Description: Report presenting drag coefficients during power-off transonic flight for the Bell X-1 airplane with a 10-percent-thick wing over a range of Mach numbers and pressure altitudes. The data was compared to an X-1 with an 8-percent-thick wing and a wind tunnel test with a 10-percent-thick wing. Information about necessary angle of attack, drag-rise Mach number, maximum lift-drag ratio, and drag coefficient at zero lift is provided.
Date: September 3, 1953
Creator: Saltzman, Edwin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Fuselage Pressures Measured on the Bell X-1 Research Airplane in Transonic Flight

Description: Report presenting pressure-distribution measurements on the fuselage of the Bell X-1 research airplane. A variety of angles of attack and Mach numbers were tested. Results regarding pressure distribution and normal load are provided.
Date: November 6, 1953
Creator: Knapp, Ronald J.; Jordan, Gareth H. & Johnson, Wallace E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at Low Speed of the Yawing Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Description: "An experimental investigation has been conducted in the Langley stability tunnel at low speed to deter+nine the yawing stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller blade angle were investigated for the complete model" (p. 1).
Date: March 31, 1953
Creator: Queijo, M. J.; Wolhart, W. D. & Fletcher, H. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Horizontal-Tail Load Measurements at Transonic Speeds of the Bell X-1 Research Airplane

Description: Report presenting a flight investigation to determine horizontal-tail loads at transonic speeds of the Bell X-1. The tests were made through the transonic region and at high lift coefficients. Results regarding the time histories, tail load data, aerodynamic-center positions, and potential load discrepancy explanations are presented.
Date: September 1, 1953
Creator: Rogers, John T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effects of Extensible Rocket Racks on Lift, Drag, and Stability of a 1/10-Scale Rocket-Boosted Model of the McDonnell XF3H-1 Airplane for a Mach Number Range of 0.60 to 1.34 : TED No. NACA DE 31

Description: Memorandum presenting the results of a test on the transonic longitudinal characteristics of a scale rocket model of the McDonnell XF3H-1 airplane. The model, flown with a center-of-gravity location of 28.5 percent of the mean aerodynamic chord and a stabilizer setting of -5.91 degrees relative to the wing chord plane, was equipped with extensible rocket racks. Results regarding the Reynolds number, rocket-rack program, flight time history, trim, lift, drag, longitudinal stability, directional … more
Date: June 16, 1953
Creator: Crabill, Norman L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Tests of a 0.13-Scale Model of the Convair XFY-1 Vertically Rising Airplane in a Setup Simulating that Proposed for Captive-Flight Tests in a Hangar, TED No. NACA DE 368

Description: "An experimental investigation has been conducted to determine the dynamic stability and control characteristics of a 0.13-scale free-flight model of the Convair XFY-1 airplane in test setups representing the setup proposed for use in the first flight tests of the full-scale airplane in the Moffett Field airship hangar. The investigation was conducted in two parts: first, tests with the model flying freely in an enclosure simulating the hangar, and second, tests with the model partially restrai… more
Date: 1953
Creator: Lovell, Powell M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at Low Speed of the Pitching Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373

Description: An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the pitching stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient, control deflections, and propeller blade angle were investigated. The tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, n… more
Date: July 23, 1953
Creator: Queijo, M. J.; Wolhart, Walter D. & Fletcher, H. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of the Stability and Control Characteristics of a 0.13-Scale Model of the Convair XFY-1 Vertically Rising Airplane During Constant-Altitude Transitions, TED No. NACA DE 368

Description: "An investigation is being conducted to determine the dynamic stability and control characteristics of a 0.13-scale flying model of the Convair XFY-1 vertically rising airplane. This paper presents the results of flight tests to determine the stability and control characteristics of the model during constant-altitude slow transitions from hovering to normal unstalled forward flight. The tests indicated that the airplane can be flown through the transition range fairly easily although some diffi… more
Date: 1953
Creator: Lovell, Powell M., Jr.; Kirby, Robert H. & Smith, Charles C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Spinning and Tumbling Characteristics of a 1/25-Scale Model of the Lockheed XFV-1 Airplane in the Langley 20-Foot Free-Spinning Tunnel

Description: "An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/23-scale model of the Lockheed XFV-1 airplane to determine the effects of control setting and movement upon the erect-spin and recovery characteristics for a range of airplane loading conditions. A windmilling propeller was simulated on the model for some of the tests. The investigation included determination of the size of tail parachute required for emergency recovery from demonstration spins" (p. 1).
Date: August 21, 1953
Creator: Lee, Henry A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Brief Investigation of the Hydrodynamic Characteristics of a 1/13.33-Scale Powered Dynamic Model of a Preliminary Design of the Martin XP6M-1 Flying Boat, TED No. NACA DE-385

Description: The hydrodynamic characteristics of a preliminary design of the Martin XP6M-1 flying boat have been determined. Longitudinal stability during take-off and landing, resistance of the complete model, and behavior during taxiing and landing in rough water are presented.
Date: October 21, 1953
Creator: Blanchard, Ulysse J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effects of Extensible Rocket Racks on Lift, Drag, and Stability of a 1/10 Scale Rocket-Boosted Model of the McDonnell XF3H-1 Airplane for a Mach Number Range of 0.60 to 1.34

Description: Report presenting testing of the transonic longitudinal characteristics of a model of the McDonnell XF3H-1 airplane. The model had a center-of-gravity location of 28.5 percent of the mean aerodynamic chord and a stabilizer setting of -5.91 degrees relative to the wing chord plane with extensible rocket racks. Results regarding Reynolds number, rocket-rack program, flight time history, trim, lift, drag, longitudinal stability, directional stability, and inlet pressure recovery are provided.
Date: June 16, 1953
Creator: Crabill, Norman L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Transonic Wind-Tunnel Investigation of the Trim and Dynamic Response Characteristics of the Horizontal Tail of a 1/7-Scale Model of the Complete Tail of the Grumman XF10F-1 Airplane

Description: "An investigation was made of the trim and dynamic response characteristics of the free-floating horizontal tail of a 1/7-scale model of the complete tail of the Grumman XF10F-1 airplane in the Langley 8-foot transonic tunnel at Mach numbers up to 1.13. The complete tail was mounted in the tunnel on a 3 degree conical support body. Various configurations were investigated. A loss in damping of the horizontal tail at transonic speeds was shown by both tunnel and flight tests" (p. 1).
Date: April 28, 1953
Creator: Luoma, Arvo A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Results of a Power-on Flight of a 1/10-Scale Rocket-Propelled Model of the Convair XF2Y-1 Airplane at a Mach Number of 1.53

Description: Report discussing testing on a scale model of the Convair XF2Y-1 airplane with solid-fuel rocket motors that simulate full-scale turbojet-engine characteristics at a height of 35,000 feet with full afterburning at Mach number 1.53. The model was found to have dynamic lateral instability, but these results were not likely to be found in a full-scale airplane. Information about the pitching moment, directional stability, lift-curve slope, and drag coefficients is provided.
Date: September 28, 1953
Creator: Bland, William M., Jr. & Nelson, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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
Partner: UNT Libraries Government Documents Department
open access

Geology of the Shinarump No.1 Uranium Mine, Seven Mile Canyon Area, Grand County, Utah

Description: Report discussing a geological study that took place from January 1952 - April 1953 to determine the habits, ore controls, and possible origins of the uranium deposit of the Shinarump No. 1 mine, which is located approximately 12 miles northwest of Moab, Utah.
Date: October 1953
Creator: Finch, W. I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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