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  • 1
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    Charts for Estimating the Effects of Short-period Stability Characteristics on Airplane Vertical-acceleration and Pitch-angle Response in Continuous Atmospheric Turbulence (1957)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-3992
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Comparison of Experimental and Theoretical Static Aeroelastic Loads and Deflections of a Thin 45 deg Delta Wing in Supersonic Flow (1961)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Wind tunnel tests showing the effects of static aeroelasticity for a thin 45 degree delta wing in supersonic flow are presented and compared with theory in the Mach number range 1.30 t o 4.00. Calculated deformations, normal-force coefficients, and pitching-moment coefficients based on a linearized potential theory for subsonic leading edges at a Mach number of 1.30 and a linearized potential theory for supersonic leading edges at Mach numbers of 1.64, 3.00, and 4.00 are shown to compare favorably with the wind-tunnel results. Calculations of these same deformations and coefficients based on piston theory are shown to compare satisfactorily with experiment at a Mach number of 4.00 but not so well at a Mach number of 3.00. A factor modification of piston theory is suggested which improves the correlation of these results with experiment and also with the potential-theory results.
    Keywords: Aerodynamics
    Type: NASA-TN-D-974 , L-1496
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Evaluation of Several Approximate Methods for Calculating the Symmetrical Bending-Moment Response of Flexible Airplanes to Isotropic Atmospheric Turbulence (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Several approximate procedures for calculating the bending-moment response of flexible airplanes to continuous isotropic turbulence are presented and evaluated. The modal methods (the mode-displacement and force-summation methods) and a matrix method (segmented-wing method) are considered. These approximate procedures are applied to a simplified airplane for which an exact solution to the equation of motion can be obtained. The simplified airplane consists of a uniform beam with a concentrated fuselage mass at the center. Airplane motions are limited to vertical rigid-body translation and symmetrical wing bending deflections. Output power spectra of wing bending moments based on the exact transfer-function solutions are used as a basis for the evaluation of the approximate methods. It is shown that the force-summation and the matrix methods give satisfactory accuracy and that the mode-displacement method gives unsatisfactory accuracy.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-18-59L , L-143
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Determination of the Required Number of Randomly Spaced Communication Satellites (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation has been made f o r determining the minimum number of passive satellites i n near-earth orbits required t o provide given percentages of communication time between two selected ground stations. The study is limited to the geometrical and probability aspects of the problem. An application of the analysis i s made f o r an assumed transatlantic communication system. The satellites are considered t o be i n circular, randomly spaced orbits with fixed inclination and altitude considered range from 1,000 t o 3,000 statute miles.
    Keywords: Communications and Radar
    Type: NASA-TN-D-619 , L-1067
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Space Shuttle Missions Summary (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This document has been produced and updated over a 21-year period. It is intended to be a handy reference document, basically one page per flight, and care has been exercised to make it as error-free as possible. This document is basically "as flown" data and has been compiled from many sources including flight logs, flight rules, flight anomaly logs, mod flight descent summary, post flight analysis of mps propellants, FDRD, FRD, SODB, and the MER shuttle flight data and inflight anomaly list. Orbit distance traveled is taken from the PAO mission statistics.
    Keywords: Astronautics (General)
    Type: NASA/TM-2011-216142 , PB2012-101183 , JSC-CN-19705
    Format: application/pdf
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