STELLA: Self-Reflective Terminology-Aware Framework for Building an Aerospace Information Retrieval Benchmark
Paper • 2601.03496 • Published
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aeronautics/07484_100.txt | e the porous cylinder is located below the model centerline,the NO flows mostly below the model centerline. A small amount of NO mixes or diffuses around to the top half ofthe flow, thereby weakly visualizing the top wake region and shear layer as well.
Although not shown here, a comparison was made of two nearly ident... | |
aeronautics/14162_75.txt | m light speckles are an unpredictable variable that have a great affect on the CPC technique.
The SPC technique on a larger viewing screen is superior to the CPC technique in distinguishing when the laser beam goes through the center of the simulated shock. The SPC technique results, as seen in Figure 17, are consiste... | |
aeronautics/21141_83.txt | xhibit, Reno, NV, Jan. 2007. 9 Broeren, A.P., Busch, G., and Bragg, M.B., “Aerodynamic Fidelity of Ice Accretion Simulation on a Subscale Model,” SAE 2007 Transactions: Journal of Aerospace, Vol. 116, Aug. 2008, pp. 560-575. 10 Broeren A.P., Diebold, J.M., and Bragg, M.B | |
aeronautics/23063_7.txt | t devices, such as flaps and slats, constituting the primary sources[3].
Development and maturation of viable technologies that substantially reduce the airframe component of aircraft noise is of importance to the NASA Aeronautics Research Mission Directorate (ARMD). A major effort on airframe noise reduction was init... | |
aeronautics/04502_138.txt | sused, there is residual twist of about 1.2 deg over the spanof the model. No wind tunnel corrections were applied tothe data. The reference chordline used in testing theSC1094 R8 airfoil was the SC1095 chordline. Thus, theangle-of-attack data for this airfoil have been shifted by–1 deg to allow comparison with the oth... | |
aeronautics/00718_71.txt | n that in the combustor and lagged thecombustor pressure by approximately 40 degrees.
This mode was also observed at the other two, lowerpower, operating conditions, although at smaller amplitudesand lower frequencies, as shown in Fig. 10.
ANALYSIS OF RESULTS
Comparison with Analytical Results
The experimental results ... | |
aeronautics/02024_128.txt |
plicated chemical pathways of possible interest, and/orearly jet or late plume chemistry. The transition regimebetween plume models and 3-D global models presentsa particular challenge given the potential importance ofturbulent mixing and large species fluctuations occurring on scales below typical grid lengths, of or... | |
aeronautics/20987_37.txt | n the direction of flight, Y positive to the left of the flight path, and Z positive up. With the aircraft directly overhead of the reference microphone at an altitude of 100 feet above ground level (AGL), the microphone spacing was designed to provide approximately 10° angular resolution, up to 10° below the horizon. ... | |
aeronautics/23457_13.txt | (PSL) as part of a series of fundamental icecrystal icing tests in 2018. The purpose of the aerothermal calibration test was to characterize the cloudoff temperature and flow of the PSL test facility prior to performing the cloud-on icing experiments. This report presents the temperature measurements and analysis of th... | |
aeronautics/03202_67.txt | e used to express each multivariaterthogonal function in terms of ordinary multivariateolynomials
The orthogonal functions are generated in aanner that allows them to be decomposed withoutbiguity into an expansion of ordinary multivariateolynomials. The orthogonalization process can bepeated using arbitrary ordinal, mu... | |
aeronautics/23075_128.txt | p. 487–526.doi:10.1146/annurev.fl.20.010188.002415.[30] El-Hady, N., “Spatial Three-Dimensional Secondary Instability of Compressible Boundary-Layer,” AIAA Journal, Vol. 29,No. 5, 1991, pp. 688–696. doi:10.2514/3.10642.[31] Ng, L., and Erlebacher, | |
aeronautics/10307_42.txt | m the thin film gages and phosphor.
The spacing between the pressure ports was 0.20-inches from center to center. This spacing was not dense enough to guarantee that peak pressure would be measured. The number of pressure ports on the target was limited due to the small interior size of the model and the sizing of th... | |
aeronautics/23913_90.txt | M with one or more auto generated, amended operation plans that divert the aircraft to alternate vertiports. The alternate vertiport play would be necessary if the VAS informs the PSU or FM of a sudden and indefinite, or extended, vertiport closure for the arrival vertiport for one or more vehicles in the FM’s fleet | |
aeronautics/21727_84.txt | troducing downwash acceleration is one of the key changesmade to the jet analysis to represent rotor behavior. However, reality is far different from momentum theory assumptions in that the effects of a finite number of blades,tip vortices, and root cut-out play a substantial role in theresulting non-uniform inflow dis... | |
aeronautics/24056_268.txt | 6°. The increments are smaller in the landing sizing scenario than for the takeoff L/D scenario. If larger aileron deflections are feasible, the landing scenario predicts increased AFC increment, up to 0.35% (Figure 27). An alternate approach to increasing the overall wing area to reduce approach speed is to enlarge th... | |
aeronautics/00585_830.txt | eometries, with and without boundary-layer tripping, deployed at both moderate and high flap angles. The acoustic database isobtained from a Small Aperture Directional Array (SADA) of microphones, which was constructed to electronically steer todifferent regions of the model and to obtain farfield noise spectra and dir... | |
aeronautics/17969_52.txt | l.,16 the asymptotic expansion of the quantity inparentheses (for large γ) is:
This expansion can be further simplified by applying the Dowell and Bliss method,15 whereby algebraicmanipulation is used to re-write each term in Eq. 27, and applying the binomial theorem. This procedureis outlined in the appendix. The resu... | |
aeronautics/03087_38.txt | F,and freestream unit Reynolds numbers from 0.01 to0.41 million per foot. A contoured axisymmetricnozzle is used to provide nominal freestream Machnumbers from 5.9 to 6.2. The nozzle exit diameter is20 inches with the flow exhausting into an open jettest section; the nozzle throat diameter is 0.466-inch.A bottom-mounte... | |
aeronautics/18913_163.txt | m, C., Barad, M., Housman, J., and Kiris, C., “A Comparison of Higher-Order Shock Capturing Schemes Withinthe LAVA CFD Solver,” AIAA Paper 2014-1278, Jan 13-17, National Harbor, Maryland, 2014.24Hutcheson, F., Private communication, 2014.25Shur, M., Spalart, P., and Strelets, M., “ | |
aeronautics/20100_26.txt | h 1,900, 1,900, and 2,450 rotary wing flight hours. The fourth participant had logged 800 hours of rotary wing flight time. Ownship error relative to the hover location was displayed on a laptop monitor, and the pilot attempted to minimize the error using a gaming joystick. The Bedford rating scale (Ref.9) was used to ... | |
aeronautics/12710_250.txt | f the windmill four times.” In their 1928 summary of autogyro work (ref. 4), Glauert and Lock stated that “the only point which remains uncertain is the capacity of a gyroplane to descend vertically at a low speed, but the practical importance of this question should not be exaggerated.” Drop tests were consistent with... | |
aeronautics/18818_78.txt | 5 and 30 psf were also collected forsome cases. The nominal test section airspeed was
Mach 0.1162. Test data consist of force, moment,and aeroelastic deflection measurements, and werecollected during α-sweep and q∞-sweep runs. Theaeroelastic deflection measurements were providedby a VICON motion tracking system. Figure... | |
aeronautics/16608_93.txt | e farthest apart on the slat (S11) and the main wing (M1). Because there was only one KuliteTM transducer over the flap surface, the present measurements do not provide any information about the spanwise coherence over the flap surface. For the KuliteTM transducers mounted over the slat, the spanwise coherence had larg... | |
aeronautics/01788_37.txt | l speeds withreductions in drag of 20% or more shown in wind tunneltests.
FIG. 5 shows a comparison of a tractor-trailer with a shortcab and a porous skin mounted directly on the trailingsurface of the trailer and extending 10% of the total lengthof the trailer forward of the trailing surface and a tractortrailer with ... | |
aeronautics/23057_63.txt | s) if hr < 100 tor hs < 100 t, where t is the face tolerance. A metric is formed at the vertex with the eigenvalues of 1/h2n, 1/h2r, 1/h2sandeigenvectors of nˆ,rˆ, sˆ. The surface curvature metric is intersected with other geometry metric constraints at this vertex.
An example from the Japan Aerospace Exploration Agenc... | |
aeronautics/09832_88.txt | g whether the design meets requirements in many integrated vehicle areas. Many of these were described in the paper. As the Ares I design matures, with each passing month, more uses for the data output from the Monte Carlo runs are discovered as the various subsystems look for their design cases. After the design is fi... | |
aeronautics/04758_73.txt | H., “Numerical simulation of wake vortices measured during the Idaho Falls and Memphis field programs. 14th AIAA Applied Aerodynamics Conference, Proceedings, Part- II, 17-20 June 1996, New Orleans, LA, AIAA Paper No. 96-2496, pp. 943-960. 18Proctor, F. H., and Han, J | |
aeronautics/14393_71.txt | ” requiring resources in excess of those available to the general population. The nascent “personal aircraft” market is HUGE, with estimates ranging up to $1T/yearWorldwide – far larger than the current transport aircraft markets in the U.S | |
aeronautics/23249_98.txt | e small. Now, applying BEMT yields the result that the inflow angle is calculated from
where (a) is the lift curve slope of the airfoil commonly taken as 5.73 per radian and (x) is the nondimensional blade radius station, calculated as x = r/R. Knight and Hefner saw that the blade element of attack would then appear as | |
aeronautics/02024_48.txt | d range found in the direct numerical simulation study of Spalart and Wray [1996]. In previouswork we have found little variation of the basic wakedecay (rate of wake dispersion, overall vertical and horizontal extent, wake lifetime, etc.) with downstreamdomain size. The intcraction between a given Crow period and its ... | |
aeronautics/25132_56.txt | y discussed algorithms. With knowledge of the efficiency of each EE string, the healthier strings, i.e., the ones that require less overall power and will therefore cause less wear and tear on the GTE, can be utilized more heavily. Figure 12 shows the same scenario as Figure 11, but accounts for the efficiency of each ... | |
aeronautics/23785_151.txt | g from the proprotor, and can ultimately lead to negative damping (i.e., instability). In order to achieve reliable predictions, extra care must be given to dynamic load cases such as proprotor whirl flutter (for a recent example with hingeless proprotors, see Ref. [33]). Inattention to seemingly minordetails, such as... | |
aeronautics/08866_308.txt | PCY requires that DLIC be performed to determine the aircraft’s capability to accomplish the service.
The FLIPCY operational context and time sequence is shown in figures 59 and 60. Mapping of FLIPCY service to WCDMA functions is shown in figure 61. Appendix C—Summary of Previous Indepth Assessments
Many of indept... | |
aeronautics/03172_25.txt | d and assessed.n objective processing method is developednd utilized to determine vortex definition.
otor Model Test Description
The HART II program was conducted in theen-jet, anechoic test section of the Large Loweed Facility (LLF) of the DNW, which has an exitzzle of 8 m by 6 m that provides a 19m-long freewith a lo... | |
aeronautics/12710_503.txt | t Ames Research Center) initiated a program of theoretical and experimental research in rotor dynamics.
Robert A. Ormiston came to Ames Research Center in February 1968 after conducting PhD research on the aerodynamics of a sailwing at Princeton University, where Professor Earl Dowell read his thesis. Although his ori... | |
aeronautics/23077_20.txt | g Görtler instability. One of the interesting findings of the secondary instability computations by Li et al. [26] was the existence of a symmetric unstable mode that originated from the Mack mode instability of the unperturbed boundary layer and was subsequently distorted by the presence of increasingly stronger modul... | |
aeronautics/11863_62.txt | t on the 4BPF tone varied with sideline angle, with no overall noise reduction.
Wake filling properties of TEB address two fan noise mechanisms. Reductions in the wake defect are expected to give reductions in rotor/stator interaction tone levels. Fan broadband noise is thought to relate to flow turbulence levels, so ... | |
aeronautics/08281_114.txt | lmost no loss in numericalefficiency, since we use a CFL number of 1000. Calculations were performed for Cases 1, 9, and 10 with theRK/implicit scheme using 3 stages and CFL = 1000. The solutions were obtained with the same (moderatelyhigh aspect ratio) 320 × 64 grid used for the results of the RK/implicit scheme with ... | |
aeronautics/26388_355.txt | n aircraft design, operational efficiency, and environmental performance?
AI-Driven Passenger Flow Optimization in Airports
• Overview: This AI-driven system for optimizing passenger flow in airports relies on noninvasive sensors collecting biometric, psychometric, and spatio-temporal data to create a comprehensive, re... | |
aeronautics/18476_99.txt | . Both traffic scenarios were developed by an ATC subject matter expert and designed to provide equivalent pilot workload. In each scenario, eight intruders were scripted to progress to a self separation then collision avoidance alert, absent of pilot action, while four different intruders were scripted to progress onl... | |
aeronautics/01119_78.txt | Dow ComingDC-200Fluid)graduallythinsundertheinfluenceofsurfaceshear.Undersuitableassumptions, theslopeoftheoil surfaceat theleadingedgeof theoil issimplyrelatedto thecomponentof localskinfrictionperpendicularto theedge.Opticalinterferometryprovidesasensitiveprobefor measuringthewedgeangleof thefilm. | |
aeronautics/08342_428.txt |
Once the route is selected and modified, the ITP generates alternates for that route and a pilot task plan. If the ITP has a pilot’s log feature, it may compare the regulatory requirements for flying the mission with the capabilities and qualifications of both the aircraft and the pilot. If the pilot has flown the rou... | |
aeronautics/01266_4.txt | 100 with the CFD/DSMC overlap at a Knudsen nmnber of0.01 and the DSMC/collisionless DSMC overlap at 10. The present results include density contours, density and temperature along the stagnation streamline for all cases, andstagnation pressure and heat transfer coefficient as a function of Knudsen number.
Nomenclature... | |
aeronautics/11945_61.txt | d a final state toward the end of a maximum run time period when the model has achieved thermal equilibrium. For the unconditioned state, the temperatures at the six model locations vary significantly throughout the boundary-layer survey. The other two conditioned thermal states show much less cone temperature variatio... | |
aeronautics/15300_3.txt | s. The aircraft was sized for a 6600-lb payload anda range of 300 nm. The rotor planform and twist were optimized for hover and cruise performance. For the presentrotor performance calculations, the collective pitch angle is progressively increased up to and through stall with theshaft angle set to zero. The effects of... | |
aeronautics/12917_56.txt | 8, Berlin, Germany. [2] Hirt, S.M. and Anderson, B.H., “Experimental investigation of the application of microramp flow control to an oblique shock interaction”, AIAA Paper 2009-919, 47th Aerospace Sciences Meeting, January 5-8, Orlando, FL. [3] Ford, C.W.P. and Babinsky, H., “Micro-ramp control of oblique shock wave /... | |
aeronautics/22224_9.txt | nfiguration. The former nomenclature, rather than the latter, will be used herein.
The remote measurement approach utilizing an ITP is a reasonably well-established method for measurement underconditions that the transducers cannot directly tolerate [10, 11]. However, the experimental determination/validation ofa trans... | |
aeronautics/12710_60.txt | .................................................. 33Houbolt and Brooks .......................................... | |
aeronautics/15387_80.txt | o 1.54e-15 and the rms of the SA model residuals varied from 2.61e-13 to 2.77e-13.
Figure 24 shows the grid convergence of skin friction at a specific location on the plate and the drag coefficient integrated over the plate, both of which are computed using various USM3D options described earlier. Local skin friction ... | |
aeronautics/09592_73.txt | –824, 1997.7Nadarajah, S.K., Jameson, A., “Optimal Control of Unsteady Flows Using a Time Accurate Method,” AIAA Paper2002-5436, 2002.8Nadarajah, S.K., McMullen, M., and Jameson, A., “Non-Linear Frequency Domain Based Optimum Shape Design forUnsteady Three-Dimensional Flow,” AIAA Paper 2006-1052 | |
aeronautics/09416_41.txt | d at ~420 sec). However, the LES winds result in a largest angle of attack at touchdown. Note that the parachute trims near 10 deg total angle of attack. Since the aerodynamics of the parachute dominates the capsule/parachute combination, the parachute attitude is reflected in the trim attitude of the capsule as well. ... | |
aeronautics/20574_39.txt | tions were not producing the expected improvements in pressure distribution near the outboard side edge of the flap. The pressure history at the dynamic sensor locations was obtained for the last 34k time steps. These results were processed in the same manner as those for the enriched grid for PSD distribution over 8 o... | |
aeronautics/20534_38.txt | (F) sweep and a reverse (R)sweep both existed, the iterative procedure determined the optimum ∆αprb and ∆βprb such that (αprb)F + ∆αprb,(αprb)R + ∆αprb, (βprb)F + ∆βprb, and (βprb)R + ∆βprb, when rotated through ΘP to the tunnel coordinate system,would minimize the | |
aeronautics/19872_13.txt | s of CFD results. A variety of grid systems (both structured and unstructured) were used. Trends due to flap angle were analyzed, and effects of grid family, grid density, solver, and turbulence model were addressed. Some participants also assessed the effects of support brackets used to attach the flap and slat to the... | |
aeronautics/23519_19.txt | bility to simulate the break-up and heat transfer effects inside the engine [22-24].
This presentstudy looks at a different engine geometry with a hidden core design. The research engine was never in production so there are not any known ice-crystal icing issues. Therefore it provided an ideal testbed for the 1DIcing ... | |
aeronautics/10769_87.txt | 3(a).
V.A.2. Spanwise Periodic Roughness Arrays: DREs
The definition of a spanwise periodic array of roughness elements has at least four independent parametersthat can be optimized to accomplish a desired effect; 1) the roughness size and shape (e.g. cylindrical withradius r), 2) the roughness spacing (i.e. wavelengt... | |
aeronautics/10768_11.txt | nwell-known upwind schemes that utilize a 1D approximate Riemann solver at cell interfaces. Unique flow dependent variables determined by the Riemann solver are required at these cell interfaces to integrate the governing conservation laws over the discretized domain. When applied to multi-dimensional flows, such one-d... | |
aeronautics/00428_647.txt | d tests are discussed to explain the capabilities this facility provides and to demonstrate the experience of thestaff.
down Wind Tunnels; Propulsion System P erformanc e; Flight Simulation; Aerodynamic Heatin
The Wall Interference Correction System (WICS) is operational at the National Transonic Facility (NTF) of NASA... | |
aeronautics/15680_4.txt | ssed, along with the status of FY14 efforts and future plans.
I. Introduction
The field of Avionics is advancing far more rapidly in terrestrial applications than in space flight applications. Spaceflight Avionics are not keeping pace with expectations set by terrestrial experience, nor are they keeping pace with the... | |
aeronautics/11355_23.txt | r the downwash study, a set of three consistently sized grids with varying tail incidences weregenerated. For the tail-off configuration, the tail solid surfaces were removed, and the volume grid was re-generatedwith the same spacing requirements in the location of the tail as were used in the tail-on configuration. A ... | |
aeronautics/16144_68.txt | n to have minimum pressure RMS values, to establish a base noise level (PA8410m). Five Kulite® LLE-2DC-750 pressure transducers were mounted on the TA spider arms for acoustic monitoring during the Segment 2 envelope expansion flights. A perspective view, illustrating the structure of the TA, can be seen in Fig. 10; th... | |
aeronautics/19806_59.txt | tially blocked slots (Run 55) was adopted for the small separation case (case C). Another factor which can contribute to 3D effects is the fact that the channel width narrows at the upstream end of the splitter plate (from 381mm to 355mm wide) and then re-expands near the aft end of the splitter plate (from 355 mm to 3... | |
aeronautics/07420_53.txt | 2 descent phase air data, aerodynamic attitude, and control deflections arepresented in appendix A. Identified on these time histories are the segments of flight corresponding to the MSdescribed in the “Mission Description” section and table 1 above. Figures A-01 through A-05 show the comparisonsof the postflight traje... | |
aeronautics/12557_36.txt | xact match to the flight case, lying about halfway between the geometric scaled nozzles and flight. The effect of increasing the exit angle from 5° to 15° is shown in Fig. 6b. While not making a large difference in maximum plume diameter the initial plume region agrees much better. Lastly, note the dramatic increase in... | |
aeronautics/08191_19.txt | TPT (to 9 x 106)
Electromagnetic and piezo ZMF actuators
– Actuator performance degraded at large Re due topressure
– Actuators did not have sufficient authority to attach flap atrequired flap deflections
• Multiple excitation locations improve performance CFD Validation of Unsteady Flows
• Turbulent Separation Control... | |
aeronautics/15897_72.txt | ....... 37Figure 56. Integral Cap Tooling Plate Installation ........................................................................ 38Figure 57 | |
aeronautics/17943_52.txt | o data points where the engine did not experience an icing event even when the ice water content was increased. From the test data that was generated in PSL, all test data points with ice ingestion were analyzed utilizing the computer models described in Section I (Figure 3). An engine icing event caused by ice accreti... | |
aeronautics/22462_2.txt | yton engine with that of a Stirling engine to create a highly efficient recuperating gas turbine engine. In the explored case, both Brayton cycle and Stirling cycle engines are used to generate electrical power. Additionally, the Stirling engine is used to draw heat out of the Brayton turbine (acting to cool the turbin... | |
aeronautics/23830_116.txt | 2006, https://doi.org/10.2514/6.2006-206.3. Grzych, M. and Mason, J., “Weather Conditions Associated with Jet Engine Power Loss and Damage due to the Ingestion of Ice Particles: What We’ve Learned Through 2009,” in AMSMeeting, Jan. 2010, https://ams.confex.com/ams/90annual/techprogram/paper_165923.htm.4. Mason, J | |
aeronautics/03683_54.txt | y.
Accumulation Parameter, Ac
The accumulation parameter directly determines the quantity of ice produced. In scaling calculations, the matching of scale and reference Ac (see eq. (4)) allows the determination of the scale spray time. In principle, time can be set easily in test facilities, so that there is no need fo... | |
aeronautics/22920_337.txt | g n-alkyl chain component of the mixed C7A compositions upon ARF were temperature dependent. The C11A/C7A (50/50) and C5MEG/C7A (50/50) surfaces would be presumably in a “fluid-like” state based on the melting point of the analogous compounds (Tables 4 and 5). The 1-decanol (i.e | |
aeronautics/01024_289.txt | rison with two-dimensional analyses. Notethat there is no experimental data available for thisconfiguration.
The parameters for this configuration are such thatthe mid-span location corresponds to a flat platecascade with a stagger angle of 45 degrees, unit gapto-chord ratio, operating in a uniform mean flow at aMach n... | |
aeronautics/24261_43.txt | y. We define conflicts as when two or more flightsare projected to arrive at around the same time. For the purpose of this project, we used a window of 2 minutes. Thissituation can occur for a multitude of reasons (early or delayed flights, deviations due to weather, reduced runwaycapacity, etc.). If a conflict arises,... | |
aeronautics/26345_149.txt | imented with introducing an additional angle of attack design variable for two of the drag minimization optimizations.
For all cases, the lift coefficient was constrained to a specified target to ensure sufficient lift for steady level flight. A structural KS stress aggregation function was also applied to all problems... | |
aeronautics/10979_9.txt | s chemistry, were clearly defined within the matrix of simulations performed to define the aerodatabook.
Support of aerothermal design for the Orion entry capsule and more recent robotic entry vehicles to Marshave brought new simulation and validation needs to the forefront. Reaction control system jets fired fromthe b... | |
aeronautics/22970_70.txt | d SRB data has been rotated in Fig. 23(when compared to the view in Fig. 21) to get the best magnification factor for the figure. The upper surface data ofFig. 23a show symmetric flow over and between the forward port and starboard SRBs.
Another area where the CFD predicts a larger absolute value of CP presence than th... | |
aeronautics/22253_46.txt | xuê T|xGê pN>(Tê 9Y+êp
ê $ê xΫ¦«Â¸ê Ypê ¹«ÎÓ«ÇÂê ÈÓê Ç£ê 2(,>ê
The first calibration data set comes from a machine calibration of NASA’s MC60E balance | |
aeronautics/03702_52.txt | l-scale, 72-in.-chord NACA 23012 wing section.
Test Facility
The IWT (fig. 3) is an atmosphericpressure, closed-loop refrigerated tunnel measuring 40 ft by 70 ft overall. It has an external 200-hp electric motor driving a 79-in.-diameter axial fan to provide wind velocity, a 70-ton-capacity refrigeration system for co... | |
aeronautics/25124_28.txt | g., for two quantity ofinterest vectors in the (𝛼 , 𝛽) space
2) compute the average range of residuals within data groups of interest, e.g., from a residual range space𝑅(𝛼, 𝛽) = | ®𝑞1 − ®𝑞2| all 𝛽 measurements may be averaged together to yield an average residual range space 𝑅¯(𝛼);3) approximate the standard ... | |
aeronautics/22253_7.txt | 1 = forward normal force component of a force balanceN2 = aft normal force component of a force balancePM = pitching moment of a balanceRM = rolling moment of a balanceSF = side force of a balanceS1 = forward side force component of a force balanceS2 = aft side force component of a force balanceYM = yawing moment of a ... | |
aeronautics/14019_8.txt | d of discontinuities for systems of stiff reacting flows remain a challengefor algorithm development [15].
In addition to the minimization of numerical dissipation while maintaining numericalstability in compressible turbulence with strong shocks, Yee & Sjogreen and Yee & Sweby ¨[19, 20, 16] discussed a general framewo... | |
aeronautics/12578_533.txt | AIAA–1984–109), 1984.48. Desplas, P.: F1 Pressurized Subsonic Wind Tunnel User’s Guide. Large Technical Facilities, Le Fauga-Mauzac Wind Tunnels Departement, ONERA, France, 1998. 49. Moëns, F.: SUNSET Project: Numerical Investigations for the Preparation of the F1 Test Campaign. ONERA Technical Report No. RT 1/12405 DA | |
aeronautics/10870_26.txt | e floating wind turbine system shown in FIG.1 thatincludes a structural guy post and guy cables.
5 FIG. 6 is a perspective view of another alternate embodiment of the floating wind turbine system shown in FIG.1 thatincludes a pivotable connection between the rotor blades andthe rotor hub.
FIG. 7 is a perspective view o... | |
aeronautics/18498_54.txt | 3, NPRc = NPRb = 1.8, and NTRc = 3.0 are shown in Figure 6 for a range of NPRt. The data for 100 and 140 have been offset 5 and 10 dB, respectively. For NPRt = 2.1, the velocities of the two outer streams are inverted since the tertiary-stream velocity is greater than that of the bypass stream | |
aeronautics/13327_46.txt | , which results in bounds that quantify the potential error in the output for a given input, i.e.,a magnitude error or ‘vertical’ uncertainty. The article by Hemsch et al.13 describes in detail the processinvolved in the estimation of aerodynamic uncertainties for the Ares I launch vehicle during the ascent phaseof fli... | |
aeronautics/14703_89.txt | s, ε i (i = 0, 1, 2, 3, ..., n) , at the i-th strain stations needed for inputs to calculate the beam deflections were generated by converting the SPAR-generated axial nodal stresses, σi (i = 0, 1, 2, 3, ..., n) , at the i-th strain station into the associated bending strains, ε i , through Hooke’s law (that is, εi = σ | |
aeronautics/08986_60.txt | t test was simulated using LS-DYNA. The model is shown in Figure 15(a). The fuselage section model is the same as used in previous impact simulations. A 15-ft by 15-ft by 2.5-ft block of sand was modeled using solid elements. The material properties assigned to the sand were obtained from a model that was developed in ... | |
aeronautics/09116_9.txt | o optidly design the aconstic treatment for maximum attenuation within a specified nacelle geometry. Time domain methods are a topic of considerable research interest; however, the frequency domain method remains the primary basis for the prdction of liner attenuation in the aircraft noise industry. Although engine des... | |
aeronautics/25822_18.txt | n the sonic boom analysis methods to compute the ground signatures of the aircraft and the Ae,r target.
For any inviscid CFD solver and fixed OML with flow-through nacelles, an aircraft’s undertrack dp/p at 3BL below the aircraft is approximately invariant with respect to altitude change (see Fig. 3a) as long as the Ao... | |
aeronautics/19518_127.txt | m is where ∆τ =dτ ijdti ∆t is the transformed time step.
To linearize Eq. (60), the following identities are used:
the minimization statement in Eq. (60) by ε2 and taking the limit of ε → 0 results in
The governing equation for the shadow trajectory Q0i, Eq. (61), is linearized around the reference solutionQi,
Combinin... | |
aeronautics/17297_42.txt | gure 9d shows this concept installed on the 18% scale aircraft model. C. 14 x 22 Wind Tunnel
Acquisition of acoustic measurements and determination of the flyover directivity patterns for flap/gear noise sources required that the 14 x 22 facility be operated in an open-wall (jet) mode whereby the ceiling and the side ... | |
aeronautics/11371_72.txt | equate to conduct V & V of complex systems and that statistical validation tools are needed.
NASA Responses
The responses from NASA generally discussed subjects which could provide for improved V & V but needed additional research. These subjects included: the advocacy of probability analysis as a means to translate th... | |
aeronautics/12940_36.txt | e corotating primary vortices.
3.1.4 Shock-vortex interactions
Although shock waves constitute a separate class of flow structures, it would be remiss not to briefly address shock-vortex interactions. At transonic speeds the presence of shocks will fundamentally alter any vortex properties also present, and one examp... | |
aeronautics/12671_97.txt | g the lateral aerodynamic drag characteristics. The stability derivative basis of the q"
&&facilitated this analysis through the variation of terms such as to assess the impact of drag prediction on the lateral flapping in synthesized piloted Lateral Reposition maneuvers.
Pilot Modeling of Lateral Reposition | |
aeronautics/21892_132.txt | t axis. The higher strength vortex near the groundcan be inferred from the streamtraces in Fig. 12b as wellas by comparing the Vr velocity magnitude exhibited bythe green and magenta curves shown in Fig. 21a. The single rotor with fuselage shows larger negative Vr near theground than the isolated rotor IGE.
A stagnatio... | |
aeronautics/10330_40.txt | . The wavelength of the narrowband dye laserthat provided the second pump beam was adjusted to 561.0 nm toposition the most prominent feature of the CO, Raman spectrum,the 00°0-10°0 band, close to the nitrogen bandhead. The abscissainFig. 3 correspondsto the Raman shiftregionfortheCO 2 molecule.InFig. 3,theRamanshiftN2... | |
aeronautics/09420_85.txt | , anisotropic grids that accommodate better alignment of stretchedtetrahedral cells with the wave angles.
To demonstrate the utility of the new technology for computing sonic boom problems, a generic wing-bodyconfiguration referred to as the Segmented Leading Edge (SLE) model has been employed. The model (shown inFigur... | |
aeronautics/20084_112.txt | . 23Figure 22. Simplified flowchart of airfoil adjustment code. .............................................................. 24Figure 23. Radial interpolation check of lift coefficient at M = 0.30. ................................................ 25Figure 24. Stall delay as function of angle of attack or Mach number ... | |
aeronautics/23313_174.txt | eraction between negotiation and flight priority. Participants argued that a flight that has priority status (e.g., due to a system failure) should not have to negotiate and should be allowed to fly through others’ space (as is the case currently in the UTM system). In effect, a priority flight would “win” every negoti... | |
aeronautics/17994_102.txt | 6. A gas turbine engine comprising the rotor blade of claim 55 1. 7. A rotor stage comprising a plurality of circumferentially arranged rotor blades as set forth in claim 1, wherein in operation of the rotor stage the exit pressure ratio profile has an absolute value of at least 1.3 for each of the relative span 6o he... |
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STELLA (Parquet)
telepix/STELLA 데이터셋의 HuggingFace-native Parquet 변환 버전입니다.
STELLA는 NASA Technical Reports Server (NTRS) 문서 기반 항공우주 도메인 Cross-lingual IR 벤치마크입니다.
Usage
from datasets import load_dataset
# Corpus (영어, 2.4M passages)
corpus = load_dataset("datalama/STELLA", "corpus", split="test")
# 한국어 쿼리
ko_queries = load_dataset("datalama/STELLA", "ko-queries", split="test")
# 한국어 qrels
ko_qrels = load_dataset("datalama/STELLA", "ko-qrels", split="test")
Configs
| Config | Split | Rows | Description |
|---|---|---|---|
corpus |
test | 2,405,044 | 영어 corpus (전 언어 공유) |
{{lang}}-queries |
test | 1,000 | 언어별 쿼리 (7개 언어) |
{{lang}}-qrels |
test | 1,000 | 언어별 relevance judgments |
지원 언어: en, ko, fr, id, ja, th, zh
Schema
corpus: _id (str), title (str), text (str)
queries: _id (str), text (str)
qrels: query-id (str), corpus-id (str), score (int)
Cross-lingual Evaluation
STELLA는 비대칭 cross-lingual IR 벤치마크입니다:
- Corpus: 영어 전용 (NASA NTRS 문서)
- Queries: 영어 원본 + 6개 번역 언어
- 평가: 다국어 쿼리 → 영어 corpus 검색
쿼리 유형
- TCQ (Terminology Concordant Query): 기술 용어는 영어 유지, 설명만 번역
- TAQ (Terminology Agnostic Query): 전체를 타겟 언어로 완전 번역
Corpus Categories
| Category | Passages |
|---|---|
| Space Sciences | 539,764 |
| Geosciences | 362,624 |
| Aeronautics | 306,505 |
| Engineering | 292,337 |
| Physics | 242,575 |
| Chemistry and Materials | 225,136 |
| Life Sciences | 197,600 |
| Mathematical/Computer Sciences | 130,214 |
| Astronautics | 97,773 |
| Social/Information Sciences | 10,516 |
Citation
@article{{kim2026stella,
title={{STELLA: Self-Reflective Terminology-Aware Framework for Building an Aerospace Information Retrieval Benchmark}},
author={{Bongmin Kim}},
year={{2026}},
eprint={{2601.03496}},
archivePrefix={{arXiv}},
primaryClass={{cs.IR}}
}}
License
CC-BY-4.0 (원본 STELLA 라이선스 준수)
Source
이 데이터셋은 telepix/STELLA의 포맷 변환 버전입니다.
원본 데이터의 텍스트는 변경 없이 유지되었으며, HuggingFace load_dataset() 호환을 위해 Parquet 포맷으로 변환하였습니다.
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