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  • AERODYNAMICS  (8)
  • GEOPHYSICS  (8)
  • STRUCTURAL MECHANICS  (4)
  • Female
  • 1985-1989  (20)
  • 1
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    Algebraic grid generation about wing-fuselage bodies (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: An algebraic procedure for generating boundary-fitted grids about wing-fuselage configurations is presented. A wing-fuselage configuration consists of two aircraft components specified by cross sections and mathematically represented by Coons' patches. Several grid blocks are constructed to cover the entire region surrounding the configuration, and each grid block maps into a computational cube. Grid points are first determined on the six boundary surfaces of a block and then in the interior. Grid points on the surface of the configuration are derived from the intersection of planes with the Coons' patch definition. Approximate arc length distributions along the resulting grid curves concentrate and disperse grid points. The two-boundary technique and transfinite interpolation are used to determine grid points on the remaining boundary surfaces and block interiors.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 868-872
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    NASA seat experiment and occupant responses (1986)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Results of the crash test of a remotely piloted transport aircraft instrumented to measure a NASA energy-absorbing transport seat are given. Human tolerance limits to acceleration and a dynamic response index model are discussed. It was found that the acceleration levels at the rear of the airplane were quite low and were below the stroking threshold of the NASA EA-seat. Therefore, dummies in the standard and EA-seat responded approximately the same. All longitudinal accelerations were quite low for the primary impact with very low forces measured in the lap belts. The vertical (spineward) acceleration levels measured in the dummies were also relatively low and very survivable from an impact tolerance standpoint. The pilot with an 18 G peak acceleration received by far the highest vertical acceleration and could have possibly received slight spinal injury.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center Full-Scale Transport Controlled Impact Demonstration; p 79-89
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Development of an energy-absorbing passenger seat for a transport aircraft (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Commercial air transport passenger safety and survivability, in the event of an impact-survivable crash, are subjects receiving increased technical focus/study by the aviation community. A B-720 aircraft, highly instrumented, and remotely controlled from the ground by a pilot in a simulated cockpit, was crashed on a specially prepared gravel covered impact site. The aircraft was impacted under controlled conditions in an air-to-ground gear-up mode, at a nominal speed of 150 knots and 4-1/2 deg glide slope. Data from a number of on board, crash worthiness experiments provided valuable information related to structural loads/failure modes, antimisting kerosene fuel, passenger and attendant restraint systems and energy absorbing seats. The development of an energy absorbing (EA) seat accomplished through innovative modification of a typical modern standard commercial aviation transport, three passenger seat is described.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Ames Research Center 19th Aerospace Mech. Symp.; p 39-58
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Unsteady transonics of a wing with tip store (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 662-668
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Wind-tunnel investigation of the OMAC canard configuration (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Wind-tunnel tests were conducted on a 0.175-scale model of the OMAC Laser 300 canard configuration in the NASA Langley 12-Foot Low-Speed Wind Tunnel to determine its low-speed high angel-of-attack aerodynamic characteristics. The Laser 300 is a general aviation turboprop pusher aircraft utilizing a canard configuration. The design incorporates a low forward wing and a high main wing with a leading-edge droop installed on the outboard panel and tip fins mounted on the wing tips. The model was tested over a range of -6 to 50-deg angle-of-attack and 20 to -20 deg sideslip. Static force and moment data were measured, and the longitudinal and lateral-directional characteristics were determined.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-2608
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Unsteady transonics of a wing with tip store (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The presence of tip stores influences both the aerodynamic and the aeroelastic performance of wings. Such effects are more pronounced in the transonic regime. In this study, a theoretical method is developed, for the first time, to compute unsteady transonics of oscillating wings with tip stores. The method is based on the small-disturbance, aerodynamic equations of motion from the potential-flow theory. To validate the method, subsonic and transonic aerodynamic computations are made for a lower-aspect-ratio wing, and they are compared with the available experimental data. Comparisons are favorable. The strong effects of the tip store on the transonic aerodynamics of the wing are also illustrated. The method developed in this steady can be used for transonic, aeroelastic computations of wings with tip stores.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-0010
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Transonic aeroelasticity of wings with tip stores (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The presence of tip stores influences both aerodynamic and aeroelastic performances of wings. Such effects are more pronounced in the transonic regime. In this study, transonic aeroelasticity of wings with tip stores is studied for the first time by a theoretical method using the unsteady-small disturbance transonic aerodynamic equations coupled with modal structural equations of motion. The aerodynamic and structural equations of motion are simultaneously integrated by a time-accurate numerical scheme. To validate the tip store simulation, aeroelastic computations are made for a typical rectangular wing with a tip store and results are correlated with available wind tunnel data for the corresponding wing without a tip store at various flight conditions. Aeroelastic computations are also made for a typical fighter wing with a tip store. Present computations show that it is important to account for the aerodynamics of the tip store, particularly in the transonic regime where the tip store can make the wing aeroelastically unstable.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-1007
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Effects of cone surface waviness and freestream noise on transition in supersonic flow (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A comparison of transition on wavy-wall and smooth-wall cones in a Mach 3.5 wind tunnel is made under conditions of either low freestream noise (quiet flow) or high freestream noise (noisy flow). The noisy flow compares to that found in conventional wind tunnels while the quiet flow gives transitional Reynolds numbers on smooth sharp cones comparable to those found in flight. The waves were found to have a much smaller effect on transition than similar sized trip wires. A satisfatory correlating parameter for the effect of waves on transition was simply the wave height-to-length ratio. A given value of this ratio was found to cause the same percentage change in transition location in quiet and noisy flows.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-1086
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Vertical drop test of a transport fuselage section located aft of the wing (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 12-foot long Boeing 707 aft fuselage section with a tapering cross section was drop tested at the NASA Langley Research Center to measure structural, seat, and occupant response to vertical crash laods and to provide data for nonlinear finite element modeling. This was the final test in a series of three different transport fuselage sections tested under identical conditions. The test parameters at impact were: 20 ft/s velocity, and zero pitch, roll, and yaw. In addition, the test was an operational shock test of the data acquisition system used for the Controlled Impact Demonstration (CID) of a remotely piloted Boeing 720 that was crash tested at NASA Ames Dryden Flight Research Facility on December 1, 1984. Post-test measurements of the crush showed that the front of the section (with larger diameter) crushed vertically approximately 14 inches while the rear crushed 18 inches. Analysis of the data traces indicate the maximum peak normal (vertical) accelerations at the bottom of the frames were approximately 109 G at body station 1040 and 64 G at body station 1120. The peak floor acceleration varied from 14 G near the wall to 25 G near the center where high frequency oscillations of the floor were evident. The peak anthropomorphic dummy pelvis normal (vertical) acceleration was 19 G's.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-89025 , NAS 1.15:89025
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    CSM Testbed Development and Large-Scale Structural Applications (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A research activity called Computational Structural Mechanics (CSM) conducted at the NASA Langley Research Center is described. This activity is developing advanced structural analysis and computational methods that exploit high-performance computers. Methods are developed in the framework of the CSM Testbed software system and applied to representative complex structural analysis problems from the aerospace industry. An overview of the CSM Testbed methods development environment is presented and some new numerical methods developed on a CRAY-2 are described. Selected application studies performed on the NAS CRAY-2 are also summarized.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-4072 , L-16499 , NAS 1.15:4072
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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