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  • AERODYNAMICS  (4)
  • AIRCRAFT STABILITY AND CONTROL  (4)
  • COMPUTER PROGRAMMING AND SOFTWARE  (1)
  • 1
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    Flight-determined aerodynamic derivatives of the AD-1 oblique-wing research airplane (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The AD-1 is a variable-sweep oblique-wing research airplane that exhibits unconventional stability and control characteristics. In this report, flight-determined and predicted stability and control derivatives for the AD-1 airplane are compared. The predictions are based on both wind tunnel and computational results. A final best estimate of derivatives is presented.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-2222 , H-1179 , NAS 1.60:2222
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    In-flight total forces, moments and static aeroelastic characteristics of an oblique-wing research airplane (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A low-speed flight investigation has provided total force and moment coefficients and aeroelastic effects for the AD-1 oblique-wing research airplane. The results were interpreted and compared with predictions that were based on wind tunnel data. An assessment has been made of the aeroelastic wing bending design criteria. Lateral-directional trim requirements caused by asymmetry were determined. At angles of attack near stall, flow visualization indicated viscous flow separation and spanwise vortex flow. These effects were also apparent in the force and moment data.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-2224 , H-1181 , NAS 1.60:2224
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Reliability analysis of an ultra-reliable fault tolerant control system (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report analyzes the reliability of NASA's Ultra-reliable Fault Tolerant Control System (UFTCS) architecture as it is currently envisioned for helicopter control. The analysis is extended to air transport and spacecraft control using the same computational and voter modules applied within the UFTCS architecture. The system reliability is calculated for several points in the helicopter, air transport, and space flight missions when there are initially 4, 5, and 6 operating channels. Sensitivity analyses are used to explore the effects of sensor failure rates and different system configurations at the 10 hour point of the helicopter mission. These analyses show that the primary limitation to system reliability is the number of flux windings on each flux summer (4 are assumed for the baseline case). Tables of system reliability at the 10 hour point are provided to allow designers to choose a configuration to meet specified reliability goals.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-166594 , NAS 1.26:166594 , REPT-8404-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A random search algorithm for laboratory computers (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The small laboratory computer is ideal for experimental control and data acquisition. Postexperimental data processing is often performed on large computers because of the availability of sophisticated programs, but costs and data compatibility are negative factors. Parameter optimization can be accomplished on the small computer, offering ease of programming, data compatibility, and low cost. A previously proposed random-search algorithm ('random creep') was found to be very slow in convergence. A method is proposed (the 'random leap' algorithm) which starts in a global search mode and automatically adjusts step size to speed convergence. A FORTRAN executive program for the random-leap algorithm is presented which calls a user-supplied function subroutine. An example of a function subroutine is given which calculates maximum-likelihood estimates of receiver operating-characteristic parameters from binary response data. Other applications in parameter estimation, generalized least squares, and matrix inversion are discussed.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: Behavior Research Methods and Instrumentation; 7; 4, 19; 1975
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Limited flight test experience with a laser transit velocimeter (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Limited flight testing of a laser transit velocimeter provided insight into the problems associated with the use of such instruments for flight research. Although the device tested was not designed for flight application, it had certain features such as fiber optics and low laser power which are attractive in the airborne environment. During these tests, operation of the velocimeter was limited by insufficient concentrations of light-scattering particles and background light interference. Normal operation was observed when these conditions were corrected by utilizing cloud particles and flying at night. A comparison between the laser flow velocity measurements and corresponding pressure measurements is presented and shows a coarse correlation. Statistical bias due to turbulence in the flow is suspected to have affected the laser measurements.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84896 , NAS 1.15:84896
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Flight-determined stability and control derivatives for the F-111 Tact research aircraft (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flight investigation was conducted to provide a stability and control derivative data base for the F-111 transonic aircraft technology research aircraft. Longitudinal and lateral-directional data were obtained as functions of Mach number, angle of attack, and wing sweep. For selected derivatives, the flight results were correlated with derivatives calculated based on vehicle geometry. The validity of the angle of attack measurement was independently verified at a Mach number of 0.70 for angles of attack between 3 and 10 degrees.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-1350 , H-1004
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Utilization of the wing-body aerodynamic analysis program (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The analysis program was used to investigate several aircraft characteristics. The studies performed included vehicle stability analysis, determination of upwash angle, identification of nonpotential flow, launch dynamics, and wake vortex upset loads. The techniques and are discussed. When possible, computed results are compared with experimental data.
    Keywords: AERODYNAMICS
    Type: NASA-TM-72856 , H-1071
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    The use of oil for in-flight flow visualization (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Oil was used to visualize inflight aerodynamic characteristics such as boundary layer transition, shock wave location, regions of separated flow, and surface flow direction. The technique, which is similar to wind tunnel oil-flow testing, involves an oil mixture to test aircraft before takeoff. After takeoff, the airplane climbs immediately to the test altitude and photographs are taken. The developmental experience is summarized, several examples of inflight oil-flow photographs are presented and discussed, and an approach for potential users of the technique is presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84915 , H-1195 , NAS 1.15:84915 , Ann. Symp. of the Soc. of Flight Test Engr.; Aug 15, 1983 - Aug 19, 1983; Newport Beach, Ca; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Ground-effect analysis of a jet transport airplane (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An analysis of the ground effect of a jet transport airplane has been made. Data were obtained from recent flight tests primarily using the constant angle-of-attack approach technique. Reasonable results were obtained for ground-effect pitching moment and lift increments. These were compared with data from other sources, including computations, wind tunnel, and previous flight test. A recommended ground-effect model was developed from the results. A brief simulator study was conducted to determine the sensitivity of a particular configuration to this ground-effect model and its associated uncertainty.
    Keywords: AERODYNAMICS
    Type: NASA-TM-85920 , H-1273 , NAS 1.15:85920 , AIAA PAPER 85-0307 , AIAA Aerospace Sci. Meeting; Jan 14, 1985 - Jan 17, 1985; Reno, NV; United States
    Format: application/pdf
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