Wind tunnel investigation of rotor lift and propulsive force at high speed. Test data appendix
For abstract, see N78-10020.
Mchugh, F.↗
SEARCH · Engineering Papers
Results for “Test Data”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Wind tunnel investigation of rotor lift and propulsive force at high speed: Test data appendix
For abstract, see N78-10020.
Mchugh, F.↗
Design of high pressure oxygen filter for extravehicular activity life support system. Volume 2: Test data
For abstract, see N78-14786.
Wilson, B. A.↗
Estimation of aerodynamic characteristics from dynamic flight test data
Significant effort was spent in estimating unknown aircraft coefficients, such as stability and control derivatives from dynamic flight maneuvers. The techniques used to estimate these coefficients are becoming increasingly complex; however, these techniques make it possible to obtain estimates of coefficients that in the past were nearly impossible to obtain. A survey of the investigations that were undertaken to obtain estimates of coefficients from dynamic flight maneuvers is presented. One method, the maximum likelihood estimation technique, is described briefly and some of the successful applications of the technique are presented. Possible techniques for analyzing responses obtained in the stall/spin regime are discussed. Recent data obtained in the stall/spin flight regime are presented along with a discussion of how some basic results can be obtained with simple analysis techniques.
Liff, K. W.↗
Acceptance test data on Hughes-USAF lightweight nickel hydrogen cells
Cell capacity, stabilization cycling, and failure analysis data on 50 A hour lightweight nickel hydrogen cells is presented and discussed.
Rogers, H. H.↗
Modification of axial compressor streamline program for analysis of engine test data
An existing axial compressor streamline analysis computer program to allow input of measured radial pressure and temperature profiles obtained from engine or cascade data is described. The proposed modifications increase the input flexibility and are accomplished without changing the computer program's input format.
Williams, J. G.↗
Synthesis of rotor test data for real-time simulation
A mathematical model of a hingeless tilting rotor is presented. The model was obtained by a systematic curve fit procedure applied to an extensive set of model scale wind tunnel data. The math model equations were used in a real time flight simulation model of a hingeless tilt rotor XV-15 to assess changes in flying qualities compared to those obtained using a previous rotor model. Extensive plots of the rotor derivatives are given. Discussions of attempts to apply multivariable linear regression technqiues to the data and the use of an analytical rotor representation are included.
Mcveigh, M. A.↗
COMSAT Labs life test data for NiH2 cells
Data concerning a ten cell nickel hydrogen battery are presented. The plates are electrochemically impregnated using slurry plaque.
Stockel, J.↗
Analysis of JP-4 fire test data and development of a simple fire model
A series of field experiments involving JP-4 fires of 7.6m dia and 15.2m dia was conducted under the sponsorship of NASA. The temperature inside the fire, the specie composition and vertical axial velocity were measured at several height locations and radial positions. The peak temperature recorded is 1400-1500 K; the velocities at 6m height are 11-12 m/s. The oxygen-to-nitrogen mass ratio along the vertical axis was found to be nearly a constant at 0.05. Significant necking of the fire was observed. A simple theoretical model was developed that predicts the experimental data on the velocity and vertical temperature distribution well. The model is based on the partial combustion of entrained air and assumed top-hat distributions for various property and flow parameters inside the fire. Quantitative agreement is obtained by using a value of 0.15 for the entrainment coefficient and 0.45 for the mixing efficiency factor. The model also predicts the fire necking.
Raj, P. K.↗
Development of an automated processing and screening system for the space shuttle orbiter flight test data
One nemesis of the structural dynamist is the tedious task of reviewing large quantities of data. This data, obtained from various types of instrumentation, may be represented by oscillogram records, root-mean-squared (rms) time histories, power spectral densities, shock spectra, 1/3 octave band analyses, and various statistical distributions. In an attempt to reduce the laborious task of manually reviewing all of the space shuttle orbiter wideband frequency-modulated (FM) analog data, an automated processing system was developed to perform the screening process based upon predefined or predicted threshold criteria.
Mccutchen, D. K.↗
Improvement of a large analytical model using test data
Previously cited in issue 13, p. 2107, Accession no. A82-30108
Berman, A.↗
Applications of model structure determination to flight test data
Several statistical and information criteria need to be considered when selecting an adequate model. Incorrect stability and control derivates result from inadequate aerodynamic model structure. Stepwise regression is used to determine the structure for an adequate model. Flight data which covers a nonlinear aerodynamic model range may be analyzed as a single data set or partitioned into several distinct sets. Stepwise regression for model structure detemination and parameter estimation was successfully applied to three aircraft types (single engine general aviation, unaugmented modern jet fighter, jet transport).
Batterson, J. G.↗
Comparing Test Data on Scale-Model Helicopter Rotors
Hovering data correlate well, but forward-flight data do not. Report compares acoustics and performance of small-scale helicopter rotor with those of full-scale rotor in both hovering and forward flight.
Kitaplioglu, Cahit↗
Evaluation of detectability and distinguishability of aircraft control element failures using flight test data
This paper examines the detectability and distinguishability of control element failures on the B-737 aircraft. The results of Weiss (1985) are used to define decentralized residuals from analytic redundancy relationships, and the results of Weiss et al. (1984) are used to define the probabilistic distance measures which provide bounds on the minimum achievable probabilities or error. The residual signals are then generated using data which were recorded during a landing approach of the NASA-Langley Advanced Transport Operations (ATOPS) transportation systems research vehicle (TSRV). The distance measures are computed using estimates of the statistics of these residual signals.
Weiss, J. L.↗
Lateral and longitudinal stability and control parameters for the space shuttle discovery as determined from flight test data
The Discovery vehicle was found to have longitudinal and lateral aerodynamic characteristics similar to those of the Columbia and Challenger vehicles. The values of the lateral and longitudinal parameters are compared with the preflight data book. The lateral parameters showed the same trends as the data book. With the exception of C sub l sub Beta for Mach numbers greater than 15, C sub n sub delta r for Mach numbers greater than 2 and for Mach numbers less than 1.5, where the variation boundaries were not well defined, ninety percent of the extracted values of the lateral parameters fell within the predicted variations. The longitudinal parameters showed more scatter, but scattered about the preflight predictions. With the exception of the Mach 1.5 to .5 region of the flight envelope, the preflight predictions seem a reasonable representation of the Shuttle aerodynamics. The models determined accounted for ninety percent of the actual flight time histories.
Suit, William T.↗
Test data acquisition system for the ESTEC large solar simulator at ESA/ESTEC
A prototype data acquisition system is described. The device characteristics, its performance and the system aspects connected to the integration of the data acquisition system into the space simulator instrumentation and environment are discussed. The data acquisition system has a modular architecture and manifold configuration capability. The input characteristics feature high resolution and accuracy/stability for the measurement of low level (thermocouple originated) analog signals, even in the presence of high common mode and S/N figures. The output is serial digital, compatible with ESA data handling standards. The device is designed to be installed in particularly hostile environments, such as that of a solar simulator.
Buroni, G.↗
Use of inelastic strain as a basis for analyzing thermomechanical test data
It was shown that the proposed data analysis method, based on inelastic strain-time response, can be used effectively to represent cyclic response at elevated temperatures for Hastelloy-X. A high level of confidence in this method was built by making comparisons of the experimental and fitted data in two forms. Because of this level of confidence, the analysis was taken one step further and inelastic strain rates were calculated from the derivatives of the fit equations.
Bartolotta, P. A.↗
National full-scale aerodynamic complex integrated systems test data system
The data acquisition system of the 80 by 120 foot wind tunnel of the National Full-Scale Aerodynamic Facility (NFAC) is described. How the various satellite data stations are connected to the data acquisition system is shown. As an illustrative example, a strain gage signal is traced from one of the satellite data locations to its final destination in the data system where the signal is processed, observed in real time on various parallel graphic displays, and stored on magnetic disks for postrun data reduction.
Jung, Oscar↗