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Correlation of Buffet Boundaries Predicted From Wind-Tunnel Tests With Those Measured During Flight Tests on the F8F-1 and X-1 Airplanes -Transonic-Bump Method

Description: Memorandum presenting testing of semispan wing-fuselage models of the F8F-1 and X-1 airplanes in the 16-foot high-speed wind tunnel utilizing the transonic-bump method. The variations of lift coefficient with angle of attack and Mach number and pitching-moment coefficient with lift coefficient at various Mach numbers are presented for the models. The buffet boundaries were found to be in reasonable agreement with those determined from flight tests of full-scale airplanes.
Date: December 24, 1952
Creator: Martin, Andrew & Reed, James F.
Partner: UNT Libraries Government Documents Department
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COMPARISON OF BULK SHIELDING REACTOR CENTERLINE MEASUREMENTS IN WATER WITH PREDICTIONS

Description: Measurements of fast neutron and gamma ray dose rates in water along the centerline of the Bulk Shielding Reactor (BSR) are compared with predictions made by use of three available computer programs. It is found that the predictions are very dependent on the assumptions made concerning power distribution and that the more accurate descriptions of the source lead to predictions that agree with measurements to within 20% throughout thickness ranges as great as 100 centimeters of water. (auth)
Date: November 1, 1958
Creator: Casper, A.W.
Partner: UNT Libraries Government Documents Department
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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.
Partner: UNT Libraries Government Documents Department
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Decontamination of the KER Rupture Experiment Loop Test Series B - Tests No. 1 and 2

Description: The first series tests in the KER-REP-1 loop proved that a fisssion product contaminated loop could be decontaminated to a safe level for contact maintenance. The second series of tests ere scheduled for a more thorough evaluation of these processes includes specific decontamination factors, process corrosion rates, loop activity reduction factors (loop decontamination factors), and any preferential decontamination which may be present.
Date: November 2, 1959
Creator: Weed, R. D.
Partner: UNT Libraries Government Documents Department
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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.
Partner: UNT Libraries Government Documents Department
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Flight Test of the Lateral Stability of a 0.133-Scale Model of the Convair XFY-1 Airplane with Windmilling Propellers at Mach Numbers from 0.70 to 1.12 (TED No. NACA DE 369)

Description: A flight test of a rocket-propelled model of the Convair XFY-1 airplane was conducted to determine the lateral stability and control characteristics, The 0.133-scale model had windmilling propellers for this test, which covered a Mach number range of O.70 to 1.12. The center of gravity was located at 13.9 percent of the mean aerodynamic chord. The methods of analysis included both a solution by vector diagrams and simple one- and two-degree-of-freedom methods. The model was both statically and … more
Date: November 9, 1955
Creator: Hollinger, James A. & Mitcham, Grady L.
Partner: UNT Libraries Government Documents Department
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Lift and drag coefficients for the Bell X-1 airplane (8-percent-thick wing) in power-off transonic flight

Description: Report presenting drag coefficients determined by the accelerometer method for the Bell X-1 airplane with 8-percent-thick wing and 6-percent-thick tail in power-off flight over a range of Mach numbers and lift coefficients. Results regarding the variation of computed lift and drag coefficients, variation of lift coefficient with Mach number, and effect of Mach number on lift-drag ratio are provided.
Date: June 25, 1951
Creator: Carman, L. Robert & Carden, John R.
Partner: UNT Libraries Government Documents Department
open access

Effects of the Lateral Oscillation of Fixing the Rudder and Reflexing the Flaps on the Bell X-1 Airplane

Description: Memorandum presenting flight tests made on the Bell X-1 airplane with the 10-percent-thick wing and the 8-percent-thick tail to evaluate the effects of fixing the rudder and changing the inclination of the principal axes of inertia. The data were obtained during power-off glides at altitudes between 32,000 and 16,000 feet.
Date: December 11, 1950
Creator: Drake, Hubert M.
Partner: UNT Libraries Government Documents Department
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Flight Measurements of the Pressure Distribution on the Wing of the X-1 Airplane (10 Percent Thick Wing) Over a Chordwise Station Near the Midspan, in Level Flight at Mach Numbers From 0.79 to 1.00 and in a Pull Up at a Mach Number of 0.98

Description: Report presenting measurements of chordwise pressure distribution over the 10-percent-thick wing of the X-1 research airplane at a section near the midspan of the left wing. Results regarding the upper- and lower-surface pressure distributions at a range of Mach numbers and section loads are provided.
Date: September 12, 1950
Creator: Carner, H. Arthur & Knapp, Ronald J.
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.
Partner: UNT Libraries Government Documents Department
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Full-scale wind-tunnel tests of the longitudinal stability and control characteristics of the XV-1 convertiplane in the autorotating flight range

Description: Force and moments were measured for the XV-1 convertiplane at 75 to 150 knots. Rotor on and off and propeller powered and off configurations were investigated. The characteristics of the V-tab horizontal tail and its downwash field were studied. Lift interference between fixed wing and rotor and possible means of drag reduction were considered.
Date: May 17, 1956
Creator: Hickey, David H.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Static Lateral and Longitudinal Stability Characteristics of a 1/62-Scale Model of the X-1E Airplane at Combined Angles of Attack and Sideslip at Supersonic Speeds

Description: Report presenting an investigation to determine the static longitudinal and lateral stability characteristics of a model of X-1E airplane at combined angles of attack and sideslip. Results regarding the static longitudinal and lateral force and moment characteristics and stability derivatives are provided.
Date: September 19, 1957
Creator: Henderson, Arthur, Jr.
Partner: UNT Libraries Government Documents Department
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Flight Characteristics of a 1/4-Scale Model of the XFV-1 Airplane (TED No. NACA DE-378)

Description: From Summary: "A 1/4-scale dynamically similar model of the XFV-1 airplane has been flown in the Ames 40- by 80-foot wind tunnel, using the trailing flight-cable technique. This investigation was devoted to establishing the flight characteristics of the model in forward flight from hovering to wing stall, and in yawed flight (wing span alined with the relative wind) from hovering to the maximum speed at which controlled flight could be maintained. Landings, take-offs, and hovering characteristi… more
Date: October 15, 1952
Creator: Kelly, Mark W. & Smaus, Louis H.
Partner: UNT Libraries Government Documents Department
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Flight Tests of a 0.13-Scale Model of the Convair XFY-1 Vertically Rising Airplane with the Lower Vertical Tail Removed, TED No. DE 368

Description: "An experimental investigation has been conducted to determine the dynamic stability and control characteristics in hovering and transition flight of a 0.13-scale flying model of the Convair XFY-1 vertically rising airplane with the lower vertical tail removed. The purpose of the tests was to obtain a general indication of the behavior of a vertically rising airplane of the same general type as the XFY-1 but without a lower vertical tail in order to simplify power-off belly landings in an emerg… more
Date: May 12, 1954
Creator: Lovell, Powell M., Jr.
Partner: UNT Libraries Government Documents Department
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Vertical Descent and Landing Tests of a 0.13-Scale Model of the Convair XFY-1 Vertically Rising Airplane in Still Air, 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 Convair XFY-1 vertically rising airplane. This paper presents the results of flight and force tests to determine the stability and control characteristics of the model in vertical descent and landings in still air. The tests indicated that landings, including vertical descent from altitudes representing up to 400 feet for the full-scale airplane and at rates of des… more
Date: March 4, 1954
Creator: Smith, Charles C., Jr. & Lovell, Powell M., Jr.
Partner: UNT Libraries Government Documents Department
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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.
Partner: UNT Libraries Government Documents Department
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Longitudinal Stability Characteristics of the Consolidated Vultee XFY-1 Airplane with Windmilling Propellers as Obtained from Flight of 0.133-Scale Rocket-Propelled Model at Mach Numbers from 0.70 to 1.13

Description: From Summary: "A flight test has been conducted to determine the longitudinal stability and control characteristics of a 0.133-scale model of the Consolidated Vultee XFY-1 airplane with windmilling propellers for the Mach number range between 0.70 and 1.13. The variation of lift-curve slope C(sub L(sub alpha) with Mach number was gradual with a maximum value of 0.074 occurring at a Mach number of 0.97. Propellers had little effect upon the values of lift-curve slope or the linearity of lift coe… more
Date: June 11, 1954
Creator: Hastings, Earl C., Jr. & Mitcham, Grady L.
Partner: UNT Libraries Government Documents Department
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Behavior of the Bell X-1A Research Airplane During Exploratory Flights at Mach Numbers Near 2.0 and at Extreme Altitudes

Description: Memorandum describing a flight program consisting of exploratory flights to determine the Mach number and altitude capabilities of the Bell X-1A research airplane. On two flights of X-1 airplane, one reaching a Mach number of about 2.44, the other a geometric altitude of about 90,000 feet, lateral stability difficulties were encountered which resulted in uncontrolled rolling motions of the airplane at Mach numbers near 2.0.
Date: September 1955
Creator: Drake, Hubert M. & Stillwell, Wendell H.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation at Low Speed of the Yawing Stability Derivatives of a 1/10-Scale Model of the Douglas A4D-1 Airplane

Description: Report discussing testing of a model of the Douglas A4D-1 to determine its low-speed yawing stability derivatives. The model was tested in clean and landing configurations with horizontal and vertical tails on and off and an investigation into the effect of slats and flaps on the wing-alone derivatives.
Date: August 25, 1954
Creator: Wolhart, Walter D. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department
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Analysis of longitudinal stability and trim of the Bell X-1 airplane at a lift coefficient of 0.3 to Mach numbers near 1.05

Description: Report presenting flight test data obtained with two Bell X-1 airplanes, one with an 8-percent-thick wing and a 6-percent-thick tail and one with a 10-percent-thick wing and an 8-percent-thick tail. Data was obtained at a variety of Mach numbers, lift coefficients, and test altitudes. Results regarding stick-fixed stability and trim changes are provided.
Date: October 9, 1951
Creator: Drake, Hubert M.; Carden, John R. & Clagett, Harry P.
Partner: UNT Libraries Government Documents Department
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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
Partner: UNT Libraries Government Documents Department
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Aerodynamic and Lateral-Control Characteristics of a 1/28-Scale Model of the Bell X-1 Airplane Wing-Fuselage Combination: Transonic-Bump Method

Description: Report discussing an investigation into the lateral-control characteristics and the pitching-moment characteristics of a scale model of the X-1 wing-fuselage configuration. Information about the estimated variation of rolling effectiveness and wing-fuselage pitching-moment coefficient is described in detail.
Date: May 5, 1950
Creator: Lockwood, Vernard E.
Partner: UNT Libraries Government Documents Department
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