National Advisory Committee for Aeronautics (NACA) - 182 Matching Results

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Theoretical Investigation of the Dynamic Lateral Stability Characteristics of the Douglas X-3 Research Airplane, Study 41-B

Description: Report presenting calculations of the dynamic lateral stability characteristics of a mock-up configuration of the Douglas X-3. The oscillations were found to be stable for all calculations investigated but would not meet the Air Force damping requirements for the majority of the conditions. The use of an autopilot was found to greatly improve oscillation damping.
Date: April 27, 1950
Creator: Bennett, Charles V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Theory of Propellers 1: Determination of the Circulation Function and the Mass Coefficient for Dual-Rotating Propellers

Description: "Values of the circulation function have been obtained for dual-rotating propellers. Numerical values are given for four, eight, and twelve-blade dual-rotating propellers and for advance ratios from 2 to about 6. In addition, the circulation function has been determine for single-rotating propellers for the higher values of the advance ratio. The mass coefficient, another quantity of significance in propeller theory, has been introduced" (p. 35).
Date: May 27, 1944
Creator: Theodorsen, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Time-History Data of Maneuvers Performed by McDonnell F2H-2 Airplane During Squadron Operational Training

Description: Report presenting preliminary results of one phase of a control-motion study program using data obtained from 276 maneuvers performed using a McDonnell F2H-2 jet fighter airplane during normal squadron operational training. Results regarding classification of maneuvers, airspeed, load factors, sideslip angle, and maximum pitching-, rolling-, and yawing-angular-acceleration variations with indicated airspeed are provided.
Date: May 27, 1952
Creator: Huss, Carl R.; Andrews, William H. & Hamer, Harold A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Characteristics of a 45 Degree Sweptback Wing-Fuselage Combination: Effect of Longitudinal Wing Position and Division of Wing and Fuselage Forces and Moments

Description: Report presenting an investigation on a body of revolution with a sweptback wing with a 0.25-mean-aerodynamic-chord point at the maximum body diameter and 1.2 mean aerodynamic chords behind the maximum diameter. The fuselage had a fineness ratio of 10, a 45 degree swept wing with an aspect ratio of 4.0, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Lift, drag, pitching moments, and angles of attack were measured at a range of Mach numbers.
Date: February 27, 1953
Creator: Hallissy, Joseph M. & Bowman, Donald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Flight Measurement of the Aerodynamic Load on the Extended Slat of the Douglas D-558-II Research Airplane

Description: Report presenting a flight investigation of the aerodynamic loads of a partial-span extended leading-edge slat on the 35-degree sweptback wing of the Douglas D-558-II research airplane. The slat normal-force coefficient was found to increase with airplane normal-force coefficient until peak slat normal-force-coefficient was reached at approximately 2.2 to 2.4.
Date: August 27, 1953
Creator: Peele, James R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Turbojet combustion efficiency at high altitudes

Description: Report presenting research on the single problem of combustion efficiency of turbojet engines at high altitudes. Representative results of investigations with turbojet combustors are presented to analyze trends regarding combustor operating variables, combustor-design variables, and fuel variables.
Date: October 27, 1950
Creator: Olson, Walter T.; Childs, J. Howard & Jonash, Edmund R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Turbojet-engine evaluation of AISI 321 and AISI 347 stainless steels as nozzle-blade materials

Description: Report presenting an investigation to evaluate the engine service performance of nozzle-diaphragm blades of AISI 321 and AISI 347 stainless steels. Data were obtained from three nozzle diaphragms alternately bladed with each of the two materials. Results regarding a visual inspection, a metallurgical examination, the mechanism of cracking, and the classification of failures are provided.
Date: February 27, 1950
Creator: Garrett, Floyd B. & Yaker, Charles
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Unsteady Normal-Force Characteristics of Selected NACA Profiles at High Subsonic Mach Numbers

Description: Report presenting a wind-tunnel investigation at subsonic Mach numbers up to 0.9 to measure the root-mean-square variation of the normal forces on 27 NACA airfoil sections. The effects of thickness-chord ratio, camber, location of minimum pressure, and leading-edge radius were investigated.
Date: May 27, 1955
Creator: Polentz, Perry P.; Page, William A. & Levy, Lionel L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Use of Two-Dimensional Section Data to Estimate the Low-Speed Wing Lift Coefficient at Which Section Stall First Appears on a Swept Wing

Description: Report discusses a procedure for estimating the wing lift coefficient for and spanwise location of the first occurrence of section stall on a swept wing. It has been modified from a method used to calculate the same information for unswept wings. The effects of split flaps, leading-edge modifications, and fences are described.
Date: July 27, 1951
Creator: Maki, Ralph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of a 1/5-Scale Model of the Ryan XF2R Airplane

Description: "Wind-tunnel tests on a 1/5-scale model of the Ryan XF2R airplane were conducted to determine the aerodynamic characteristics of the air intake for the front power plant, a General Electric TG-100 gas turbine, and to determine the stability and control characteristics of the airplane. The results indicated low-dynamic-pressure recovery for the air intake to the TG-100 gas turbine with the standard propeller in operation. Propeller cuffs were designed and tested for the purpose of improving the … more
Date: June 27, 1947
Creator: Wong, Park Y.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of horizontal tails. 5: 45 degree swept-back plan form of aspect ratio 2

Description: Report presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of a 45 degree sweptback horizontal-tail model of aspect ratio 2 and a comparison of these results with results for a model of the same aspect ratio with an unswept hinge line. Results regarding the lift and hinge-moment parameters, static longitudinal stability, effect of Reynolds number, effect of standard roughness, effect of removing elevator nose seal, and visualization of the air flow… more
Date: September 27, 1949
Creator: Dods, Jules B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Low-Speed Static and Rotary Stability Derivatives of a 0.13-Scale Model of the Douglas D-558-II Airplane in the Landing Configuration

Description: Report presenting a wind-tunnel investigation to determine the low-speed static and rotary stability derivatives of a model of the Douglas D-558-II airplane in the landing configuration. Results regarding the static longitudinal characteristics, static lateral characteristics, characteristics in rolling flow, and characteristics in yawing flow are provided.
Date: August 27, 1952
Creator: Queijo, M. J. & Wells, Evalyn G.
Item Type: Refine your search to only Report
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Zero-Lift Drag of the Chance Vought Regulus II Missile at Mach Numbers Between 0.8 and 2.2 as Determined From the Flight Tests of Two 0.12-Scale Models: TED No. NACA AD 398

Description: Report presenting testing of two scale models of the Chance Vought Regulus II missile to investigate its drag characteristics for a range of Mach numbers from 0.8 to 2.2. Due to some of the differences between the observed drag values and previous testing, the exact drag level of the configuration tested is still in question. Results regarding total drag and external drag are provided.
Date: July 27, 1954
Creator: Church, James D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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