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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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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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Free-Spinning Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane, TED No. NACA AD 395

Description: "An investigation is being conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F11F-1 airplane to determine spin and recovery characteristics and the minimum-size parachute required to satisfactorily terminate the spin in an emergency. Results obtained to date are presented herein. Test results indicate that it may be difficult to obtain an erect or inverted spin on the airplane, but, if a spin is obtained, the spin will be very oscillatory and recovery fr… more
Date: July 13, 1955
Creator: Bowman, James S., Jr.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Static Longitudinal and Lateral Stability of the Bell X-1A at Supersonic Speeds

Description: "An investigation to determine the static longitudinal and lateral stability characteristics of a 1/62-scale model of the Bell X-1A has been conducted in the Langley 9-inch supersonic tunnel. tests were made at Mach numbers of 1.62, 1.94, 2.22, 2.40, and 2.62 on the wing-body, wing-body-vertical-tail, and complete configurations. Data are presented for both the body and stability axes. Detailed analysis of the test results is omitted" (p. 1).
Date: October 27, 1955
Creator: Henderson, Arthur, Jr.
Partner: UNT Libraries Government Documents Department
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Tank investigation of the hydrodynamic characteristics of a 1/3.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with a revised forebody planing bottom : TED No. NACA DE 385

Description: From Summary: "Hydrodynamic characteristics have been determined for a 1/13.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with the forebody modified so as to increase the depth of step and the angle between the forebody and afterbody keels. Longitudinal stability during takeoff and landing in smooth water and resistance of the complete model in smooth water and in waves are presented."
Date: October 20, 1955
Creator: Blanchard, Ulysse J. & Carter, Arthur W.
Partner: UNT Libraries Government Documents Department
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Stability and drag characteristics of 1/10-scale model of the Convair XF2Y-1 airplane with open inlets containing boundary layer splitter plates as obtained in free flight at Mach numbers between 0.7 and 1.5: TED No. NACA DE 365

Description: Report presenting a scale rocket-propelled model of the Convair XF2Y-1 water-based fighter airplane in free flight in a range of Mach numbers. Results regarding stability characteristics, trim characteristics, drag characteristics, and inlet and duct characteristics are provided.
Date: April 6, 1955
Creator: Bland, William M., Jr.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of a 1/4-Scale Model of the Duct System for the General Electric P-1 Nuclear Powerplant for Aircraft

Description: Report discussing testing on a model of the General Electric P-1 nuclear powerplant to determine its internal aerodynamic characteristics. The main purposes of testing were to measure the mass-flow distribution of air, to measure the total-pressure losses for the duct components and complete model, and to determine modifications necessary to attain the desired performance characteristics.
Date: July 29, 1955
Creator: Wood, Charles C. & Henry, John R.
Partner: UNT Libraries Government Documents Department
open access

Flight determination of minimum drag of 0.11-scale rocket-boosted model of the Chance Vought XF8U-1 airplane with modified fuselage area distribution and faired inlet at Mach number from 0.82 to 1.68 : TED No. NACA DE 392

Description: Report presenting a flight test conducted to determine the minimum drag of a 0.11-scale rocket-boosted model of the Chance Vought XF8U-1 airplane with a transonic-area-rule fuselage-cross-sectional-area development. Results regarding the trim normal-force coefficient and measured drag are provided.
Date: September 26, 1955
Creator: Hastings, Earl C., Jr.
Partner: UNT Libraries Government Documents Department
open access

Tank investigation of the hydrodynamic characteristics of a 1/13.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat: TED No. NACA DE 385

Description: A tank investigation was made of the hydrodynamic characteristics of a 1/13.33-scale jet-powered dynamic model of the 160,000-pound Martin XP6M-1 flying boat. Longitudinal stability during take-off and landing, resistance of the complete model, spray characteristics, flap loads, and effect of sinking speed in smooth and rough water are presented, as well as behavior during taxiing, take-off and landing in rough water. The effect on spray of two bows and several bow-spray-strip modifications and… more
Date: April 1, 1955
Creator: Carter, Arthur W. & Blanchard, Ulysse J.
Partner: UNT Libraries Government Documents Department
open access

Free-spinning-tunnel investigation of a 1/20-scale model of the Douglas A4D-1 airplane: TED No. NACA DE 389

Description: Report presenting an investigation of the spin and recovery characteristics of a 1/20-scale dynamic model of the Douglas A4D-1 attack airplane in the 20-foot free-spinning tunnel. Erect spins and recoveries were investigated with the model in the clean condition and the loading condition, which includes a center external store with and without two external wing fuel tanks installed. Results regarding several conditions, including erect spins, no external stores, horizontal-tail incidence, 4 deg… more
Date: January 19, 1955
Creator: Klinar, Walter J.; Scher, Stanley H. & Healy, Frederick M.
Partner: UNT Libraries Government Documents Department
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Free-spinning-tunnel investigation to determine the effect of spin-recovery rockets and thrust simulation on the recovery characteristics of a 1/25-scale model of the Chance Vought XF8U-1 airplane: TED No. NACA DE 392

Description: Report presenting an investigation of a model of the Chance Vought XF8U-1 airplane to determine the effect of spin-recovery rockets on the recovery characteristics of the model. The investigation also included tests to determine the effect of simulated engine thrust on the recovery characteristics of the model. Results regarding yaw rockets, thrust-simulation rocket, and roll rockets are provided.
Date: February 7, 1955
Creator: Burk, Sanger M., Jr. & Lee, Henry A.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Results of the Determination of Inlet-Pressure Distortion Effects on Compressor Stall and Altitude Operating Limits of the J57-P-1 Turbojet Engine

Description: "During an investigation of the J57-P-1 turbojet engine in the Lewis altitude wind tunnel, effects of inlet-flow distortion on engine stall characteristics and operating limits were determined. In addition to a uniform inlet-flow profile, the inlet-pressure distortions imposed included two radial, two circumferential, and one combined radial-circumferential profile. Data were obtained over a range of compressor speeds at an altitude of 50,000 and a flight Mach number of 0.8; in addition, the hi… more
Date: May 23, 1955
Creator: Wallner, L. E.; Lubick, R. J. & Chelko, L. J.
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of the effects of altitude and inlet-pressure distortions on steady-state and surge fuel flow of the J57-P-1 turbojet engine

Description: Report presenting an investigation to determine the effects of altitude and inlet-pressure distortions on the steady-state and surge characteristics of the J57-P-1 two-spool turbojet engine in the altitude wind tunnel. Steady-state performance and surge fuel flows were obtained with a uniform inlet distribution at a range of altitudes at flight Mach number 0.8.
Date: January 21, 1955
Creator: Lubick, Robert J.; Meyer, William R. & Wallner, Lewis E.
Partner: UNT Libraries Government Documents Department
open access

A limited analysis of buffeting experienced in flight by a North American F-86A-1 airplane with and without large external fuel tanks

Description: Report presenting a limited analysis of data collected during buffeting of a North American F-86A-1 airplane with and without large external fuel tanks installed in order to explore the buffeting characteristics of the different configurations. A two-part analysis was carried out to determine the effect of the tanks on the general buffeting characteristics and to make a detailed study of the electrical and numerical frequency analysis techniques of one run.
Date: September 2, 1955
Creator: Thompson, Jim Rogers; O'Bryan, Thomas C. & Kurbjun, Max C.
Partner: UNT Libraries Government Documents Department
open access

Supplementary Investigation in the Langley Free-Spinning Tunnel of a 1/20-Scale Model of the Douglas XF4D-1 Airplane Including Spin-Recovery Parachute Tests of the Model Loaded to Simulate the Douglas F5D-1 Airplane

Description: "A supplementary investigation has been conducted in the Langley 20-foot free-spinning tunnel of a 1/20-scale model of the Douglas XF4D-1 airplane to determine the effect of only neutralizing the rudder for recovery from an inverted spin, and the effect of partial aileron deflection with the spin for recovery from an erect spin. An estimation of the size parachute required for satisfactory recovery from a spin with the model ballasted to represent the Douglas F5D-1 (formerly the Douglas XF4D-2)… more
Date: December 30, 1955
Creator: Klinar, Walter J. & Lee, Henry A.
Partner: UNT Libraries Government Documents Department
open access

Calculation of Control Rod Worth in Appr-1

Description: Seven control rods will be used in the APPR-1 instead of five as originally planned. Critical experiments evaluating the rod worth for the APPR-1 have been performed at ORNL, and calculations have been carried out by ALCO interpreting these experimental results. The calculations indicate that the capability of any four of the original five rods to shut down the cold reactor at mid-life is marginal. The calculations are summarized in this memorandum. (auth)
Date: December 23, 1955
Creator: Giesler, H. W. & Gallagher, J. G.
Partner: UNT Libraries Government Documents Department
open access

APPR Critical Experiment

Description: No Description Available.
Date: May 18, 1955
Creator: Gallagher, J. G.; Bate, R. R.; Mann, J. E. & Callihan, A. D.
Partner: UNT Libraries Government Documents Department
open access

Design Study of a Nuclear Power Plant for 100-Kw Electric and 400-Kw Heat Capacity

Description: A conceptional design study was made of a lowpower ''package'' reactor plant for the production of 100 kw of electrical power and 400 kw of heat at remote Arctic installations. The power plant steam generator is proposed to be an unmanned, heterogeneous, boilingtype reactor capable of continuous operation for extended periods. The design is based on data derived from experiments with boiling-type reactors conducted by Argorne at the Reactor Testing Station, Arco, Idaho.
Date: May 1, 1955
Creator: Treshow, M.; Snider, A. R. & Shaftman, D. H.
Partner: UNT Libraries Government Documents Department
open access

BREEDING REACTORS

Description: No Description Available.
Date: June 1, 1955
Creator: Tobias, M.
Partner: UNT Libraries Government Documents Department
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