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aeronautics/11969_100.txt | n 4, NASA LaRC, October 2008. 15 Samareh, J.: “GridTool, A Surface Modeling and Grid Generation Tool,” Proceedings of the Workshop on Surface Modeling, Grid Generation, and Related Issues in CFD Solutions, NASA CP–3291, May 9–11, 1995. 16 Pirzadeh, S.: “Unstructured Viscous Grid Generation by Advancing-Layers Method,” ... | |
aeronautics/25795_70.txt | d Means of Compliance Process for 14 CFR Part 23, 2017) [2]. As such, the AMOC provides organizations that apply for authorization for their sUAS BVLOS operations with a way to demonstrate compliance with FAA’s regulations. In general, the regulations include performance and safety standards rather than a detailed desi... | |
aeronautics/22240_180.txt | o holds for the spatiallydeveloping case. The implications for turbulence modelling and theory are significant.
For context, recall that one finds in the literature at least three conjecturedrelationships between the wall-normal derivative of the mean velocity dU/dy andthe primary shear stress −u0v0, the two quantities... | |
aeronautics/16440_16.txt | 0-in.-diameter) Mach 3 SWT has been designed and partially fabricated to support this test. The second test is a larger scale experiment that includes a complete bleed region with an impinging reflected shock wave as shown in Figure 3.
This test will be conducted in the NASA GRC 1- by 1-Foot SWT (11 SWT), which has a ... | |
aeronautics/26388_70.txt | s Political, Economic, Social, Technological, Environmental, and Legal (PESTEL) factors. Key aspects of a future state, such as green hydrogen, multiple approaches to renewable energy, significant infrastructure changes, substantial lifecycle carbon dioxide (CO2) reductions, and others, are highlighted as essential ele... | |
aeronautics/24479_52.txt | D Airliner Pilot’s Operating Manual, Hawker BeechcraftCorporation, P.O. Box 85, Wichita, Kansas, 67201-0085 USA, Sep.2008.[6] “Type-certificate data sheet for PT6A-67 series engines,” online,European Union Aviation Safety Agency, Oct. 2019. [Online].Available: https://www.easa.europa.eu/sites/default/files/dfu/PT6A 67%... | |
aeronautics/14393_363.txt | 4, parts 1 and 2, 1996 5. Bushnell, D.M. Editor, “Potential Impacts of Advanced Aerodynamic Technology On Air Transportation System Productivity”, NASA TM 109154, 1994 6. Bushnell, D.M., “ Fluid Mechanics, Drag Reduction, and Advanced Configuration Aeronautics”, NASA TM 2000-210646, 2000 7 | |
aeronautics/23585_100.txt | e PSD shows a clear dominant frequency, one could use this signal to obtaina phase averaged pressure measurement. Different methods have been proposed in theliterature for the naturally oscillating flow fields of the fluidic oscillators. Since the signalitself is a pressure signal and the averaging method is only used ... | |
aeronautics/01853_136.txt | s, and results on an infinite densitygrid were inferred using a least squares fit to the data.
Using the inferred results on an infinite density grid, the percent error can be computed foreach of the finite grid sizes. These results are tabulated in Table 3. Grid 3, which is the defaultgrid size for all the remMning co... | |
aeronautics/00618_42.txt | eror other report number. It is also advisable to cite the title and other bibliographic identification.
Avail:DOE Depository Libraries. Organizations in U.S. cities and abroad that maintaincollections of Department of Energy reports, usually in microfiche form, are listed inEnergy Research Abstracts. Services availabl... | |
aeronautics/04234_72.txt | tigated in the Hyper-X program and work isproceeding for the current X-43 program.47 Thecurrent R&T program includes a study of failure andabort scenarios for hypersonic vehicles and conceptual flight control system architecture design.
Summary
NASA is pursuing a broad range of technologies to enable development of f... | |
aeronautics/25248_38.txt | pulsor weights (wingtip and inboard) and winggeometry would impact the overall vehicle weight. A key insight from the Georgia Tech research isthat considering static loads alone is insufficient for wingtip propulsors. Static loads from a wingtippropulsor alleviate the bending moment at the root and lead to a lower wing... | |
aeronautics/16423_38.txt | e of MITs issued for arrivals in this Center, they were the predominant restrictions considered in this study. In the remainder of this section, analyses of historical arrival MITs at ATL will be presented in terms of the cause, temporal usage (e.g., daily, weekly, monthly), duration and value, and usage in conjunction... | |
aeronautics/24799_16.txt | y NASA) makes use of a single aft mounted turbofan driving arrays of wing mounted propulsors. [3] United Technologies Research Center developed a parallel hybrid turbofan design that uses battery enabled thrust assist at take-off to decrease mission fuel burn. [4] A mild hybrid study was also performed by NASA to look ... | |
aeronautics/20483_123.txt | sult for the combined rootand tip loss function F(r¯) at a given radial station is
where
and
with the coefficients within the summation using the local radial station, ¯r and the root cutout, ¯rc defined by | |
aeronautics/01024_285.txt | s of running the INTERFACE program torewrite the steady data base to the format required byLINFLUX. In step 4 the pre-processor is run. Thiswill interpolate modal values at the structural gridonto the aerogrid, for all the modes. In step 5,LINFLUX is executed for the mode of interest andfrequency. At this stage LINFLUX... | |
aeronautics/09820_43.txt | , and is part of the 8-Foot by 6-Foot Supersonic Wind Tunnel complex. The 9-ft by 15-ft wind tunnel is capable of producing test section Mach numbers up to 0.23, as well as being used for static propulsion system performance testing. Treatment-filled boxes are installed on the test section flow surfaces making the test... | |
aeronautics/14025_40.txt | 8 DCR and the simplified ET+SRBs models exhibited similar shock structures forward of the intertank. Modeling the Orbiter and detailed protuberances was not necessary to accurately predict the pressure on the LO2 ET, apart from the local differences caused by the protuberances. VI. Pressure Extraction
During the firi... | |
aeronautics/11698_40.txt | e moment coefficients computed at the balance moment center, where the forces and moments are uncorrelated.
Plots of the database modeling errors are shown in Figures 6 through 9, where the residuals computed using Eq. (9) are plotted versus Mach number. Experimental error bounds are included on these plots, to compare... | |
aeronautics/08882_514.txt | h 2007 workshop at MIT with this type of data? [Risk ID #10]
2. Please discuss the assumption that the distortion produced by the BLI inlets can be tolerated by the fans. Highcycle fatigue caused by inlet dynamic distortion is an issue, and the assumption that it can be tolerated by the threefan system downstream seem... | |
aeronautics/00993_4.txt | s of a number of selected parameters of the system aroutlined,
NOMENCLATURE
a,, Dimensionless elastic axis position measuredfrom the midchord, positive aftc. Chord length of wing, normal to the elasticaxis, 2b.C_. Lift-curve slopeh, h0 Plunging displacement and its amplitude,respectively
ly ,ll,,,m,,pn,#NP.,,go.,rs ,... | |
aeronautics/20089_325.txt | rvoelastic Wind-Tunnel Investigation Using the Active Flexible Wing Model—Status and Recent Accomplishments. AIAA Paper 1989-1168, 30th AIAA Structures, Structural Dynamic and Materials Conference, Mobile, AL, Apr. 3-5, 1989. (Also available as NASA TM-101570, Apr. 1989.) [AFW] 12. Noll, Thomas; and Perry, Boyd, III: T... | |
aeronautics/07596_104.txt | φ are developed by Sutton and Sherman, Hoffert and Lien, and summarized isection 2.3.15,1
In the charged particle continuity equations (eqs. (16) and (17)), n n n ie ie ie = − + − characterithe ionization/recombination rate. For the ionization rate, nie+ , a single step ionization model is used, where ionization i... | |
aeronautics/22555_104.txt | r factored interaction equations in the form of Equation (35):
involving any integer exponent.
By rewriting Equation (D1) in the form
By rewriting Equation (D1) in the form
and solving for the FS, the result is
Substituting Equation (D3) into Equation (23), the MS becomes References
1. Steeve, B.E.; and Wingate, R.J.: ... | |
aeronautics/11380_13.txt | , and industry.• Use common public-domain subject geometries, simple enough to permit high-fidelity computations.• Provide baseline grids to encourage participation and help reduce variability of CFD results.• Openly discuss and identify areas needing additional research and development.• Conduct rigorous statistical a... | |
aeronautics/06933_67.txt | y first exceeded 1.0 in the boundary layer near x/c = 0.0044. For successively finer grids, the location was 0.0056, 0.0099, 0,0111, and 0.0112, respectively. As will be shown next, this apparent later transition on the finer grids is a numerical artifact related to the existence of the laminar-behavior stable neutral ... | |
aeronautics/07596_255.txt | h, unlike a classical detached shock, the flow immediately behind the shock in a streamline is supersonic. Furthermore, since the flow in a streamline is compressive downstream of the shock,Bernoulli’s equation implies that the Mach number of the flow decreases along the streamline.16 Sincethe streamline is already dow... | |
aeronautics/19736_50.txt | .................................................................................. 27 5. Summary ........... | |
aeronautics/06259_231.txt | e Grant Community Resource Center at the University of Nebraska at Omaha is a vital resource for students and faculty. The Center provides an advanced learning environment for the University and community at large. Conclusion
Over the years, the NSGC has built a solid infrastructure for aerospace research and educatio... | |
aeronautics/15786_7.txt | e earth departure stage for the ARES V vehicle and the upper-stage of the ARES I vehicle. A critical test requirement for the J-2X engine was that it be tested under start/re-start conditions of 100,000 ft (or 0.16psia) simulated altitude. In addition, the A-3 altitude test facility had to be capable of testing the J-2... | |
aeronautics/02834_12.txt | tful discussions. The Supersonic Propulsion TechnologyProject Office at NASA Glenn Research Center supported this work. Computing Jet ScreechmA ComplexAeroacoustic Feedback System
Ching Y. LohTaitech, Inc.Brook Pro'k, Ohio 44142
Lermm't S. ttultgrenNational Aeronautics and Space AdministrationGlenn Research CenterCleve... | |
aeronautics/09779_83.txt | f the Puma.However, the quarter chord or chord length alone did notchange the phase.
Most of the parameters have a small influence on thepitching moment prediction. The airfoil change from thecambered to symmetric produces less negative pitchingmoment. The aerodynamic tip design shows betterpitching moment correlation.... | |
aeronautics/20635_46.txt | t the cabin and tail of the aircraft, and ballast weights to represent fuel loading in the wings. The locations of the ELTs installed onboard the Test 1 aircraft are shown in Figure 3. The total weight of the aircraft was approximately 2,000-lb. The left side of the aircraft was painted white and 1-in.-diameter black d... | |
aeronautics/19575_381.txt | lts (Table 1.14) suggest a slightly larger particle size once reduction has taken place. TPR profiles are in agreement with a larger size forming during reduction, which weakens the interaction with the support and shifts the profile to slightly lower temperatures. Extent of reduction was observed to be about 10% highe... | |
aeronautics/20616_91.txt | , W. K., Rausch, R. D., and Bonhaus, D. L., “Implicit/Multigrid Algorithm for Incompressible Turbulent Flowson Unstructured Grids,” Journal of Computational Physics, Vol. 128, No. 2, 1996, pp. 391–408, See also AIAA Paper 95–1740.11Diskin, B., Thomas, J. L., Nielsen, E. J., Nish | |
aeronautics/25092_29.txt | s are modeled in an effort to capture how an electrical system may affect turbomachinery and vice versa. EMTAT component models utilize physical parameters, efficiency maps, or power loss maps to capture relevant electrical dynamics and component losses. This model utilizes a fixed step solver iterating at a time step ... | |
aeronautics/05032_13.txt | s a strong need for themeasurement of the fluctuating velocity components in a buffetingflowfield.
This investigation represents a small part of a broad NASA wide effortto improve the fundamental understanding of aerodynamic flows athigh angle of attack. The purpose was to obtain detail flowfieldmeasurements in the vor... | |
aeronautics/20307_127.txt | e sky across a single image. As discussedabove, kite 10 has a yellow and black pattern. This patter isvery good at creating contrast with a variety of dark and lightbackgrounds, but its appearance is different over the different backgrounds. For example, only the bright yellow pattern is visible against a dark treeline... | |
aeronautics/05011_45.txt | cted during the transonic regime as there was no data available from the SC1095 experimental data. The same large decrease in the lift curve slope is seen for the SC1095 CFD results as the NACA 0012 experimental data, though the impact does not appear to be as severe for the SC1095 airfoil. The MSES data hovers on the ... | |
aeronautics/23585_59.txt | railing edge near x/c = 1.3 due to theseparated flow and the splitter plate. The inviscid flow solution of the three-dimensionalhump model [21] is also presented in this figure. The ideal (i.e., inviscid) flow over thehump model results in more flow deceleration near the leading edge of the model and moreacceleration a... | |
aeronautics/09735_57.txt | e-trailer withconsolidation wake model. However, differencesremain between the measurement and analysis.
3. Although the multiple-trailer with consolidationwake model shows good correlation on thenormal force for the BO-105 (Ref. 8), the sameanalysis shows poor correlation on the flap bendingmoment. | |
aeronautics/12675_142.txt | s (67.5% R and outboard) evenat subsonic advancing tip Mach numbers. The reversechord dynamic stall inboard appears to be a key contributor to the retreating side impulse in torsion loading. The advancing side supersonic flow outboard appears to be a key contributor to large elastic twist deformations. The consequent h... | |
aeronautics/06259_115.txt | e experiences preparing students for future careers in the STEM disciplines. Aerospace Research (Goal 2)
research throughout the state. Research endeavors are consistent with NASA aims, driven by collaborative relationships between Nebraska and NASA researchers, nationally competitive in terms of quality and impact, a... | |
aeronautics/07596_15.txt | w at 10,000 ft With a 0.9-eV Source .................................. 6
Appendix B—Approximate Analy Density Ratios .............................................................................
C.1 Shock Angle and Downstream Flow ...................................................................................... 69... | |
aeronautics/13740_24.txt | s, frames, ribs, spars and floors, wing skins, spars and ribs,
vertical stabilizer, movable control surfaces, high-lift devices, and bulkheads. Structural cutouts were included for landing gear doors and cargo doors (Fig. 5). The total number of elements in the vehicle model is approximately 44,000, representing more ... | |
aeronautics/16026_105.txt | C. Comparison of Measured and Simulated Streamwise Velocity Profiles with Hemispherical Roughness
Figures 11a - 11e show the measured streamwise velocity profiles (black data points) compared with simulated streamwise velocity profiles without air injection (solid green lines) with a side-view orientation at spanwise... | |
aeronautics/25784_19.txt | a uniform flow at the exit. The plug nozzle is attached to the end of the floating plenum. Further details of the experimental setup can be found in past publications, e.g., (Refs. 8 and 9).
A cross-sectional view of the plug nozzle assembly, with relevant dimensions, is shown inFigure 1(b). In the present experiment,... | |
aeronautics/19470_2.txt | ‡ and Michael D. Beyar§The Boeing Company, Huntington Beach, CA, 92647
The NASA Environmentally Responsible Aviation (ERA) Project sponsored a series of computational and experimental investigations of the propulsion and airframe integration issues associated with Hybrid-Wing-Body (HWB) or Blended-Wing-Body (BWB) confi... | |
aeronautics/12640_22.txt | y that solves the RANS equations for continuum flow, including finite-rate chemistryand thermal non-equilibrium. In the present study, thethermally- and calorically-perfect RANS equations forair are solved implicitly with 1st-order time accuracy. Inviscid fluxes are formed via a modified Steger-Warmingflux vector split... | |
aeronautics/23530_209.txt | , given the very different looking UHR field (discussed in previous section), it is somewhat surprising. Also, worth pointing out is the low value of the convective speed (less than 0.5UREF) compared with the convective speed for the N+3 climb and SLTO pilot zone (~1UREF). These different values are due to the differen... | |
aeronautics/11152_7.txt | e to on.s assessodynamstacking ady premethods e-side bic turbiny for the
HPT bconsisat th ft the fAn exisas a baas a bainteracMethod Ae 3D StOf the pressuTransoaccura | |
aeronautics/22966_34.txt | e AFRL experiments [16] with variablebluntness, 7-degree half-angle cones. For this problem, the computational coordinates are defined as an orthogonal, bodyfitted coordinate system, with (ξ, η, ζ ) denoting the streamwise, wall-normal, and azimuthal coordinates, respectively,and (u, v, w) representing the correspondin... | |
aeronautics/22221_4.txt | d stability equations(PSE), in conjunction with partial-differential-equation-based planar eigenvalue analysis.The overall effect of streaks is to reduce the peak amplification factors of instability waves,indicating a possible downstream shift in the onset of laminar-turbulent transition. Thepresent study confirms pre... | |
aeronautics/00804_352.txt | yright; Avail: CASI; A03, Hardcopy; A01, Micr
Noise levels in the NUH-60 (Black Hawk) Aeromed Flight Simulator located at the U.S. Army Aeromedical ResearchLaboratory were measured. Noise levels were adjusted using a nine-position control set by the simulator operator. The simulatoroperator's manual stated that noise l... | |
aeronautics/23249_88.txt | n the aerodynamic, characteristics of the blades may ultimately be the determining factor in selecting blade aspect ratio. A very important point to note about Landgrebe’s example is that the tip Reynolds number varied considerably (548,000 to 959,500). But two sets of data were tested at a tip Reynolds number of 548,0... | |
aeronautics/18935_21.txt | e used that allows for the generation of 95% confidence intervals for the predicted met
2
ric. The cost function for this impedance optimization is based on in-duct, near-field, and/or far-field results. For example, in one embodiment, the optimum may be based on maximum in-duct attenuation. However, acoustic radiatio... | |
aeronautics/20063_183.txt | 0]). 10 below lists the result of the calculation of the lift slope for the three chosen aircraft
The overall magnitude of the authors’ theoretical lift slope estimates for the three chosen aircraft can bevalidated by comparing them with results for similar aircraft that are reported in the literature. For example,lift... | |
aeronautics/22991_17.txt | l of the array elements must be employed. Two methods were utilized during ARM III for health monitoring:
1. Multiple ground-based sound sources were embedded in the array at known locations that could be operated either independently or in unison to excite the array elements on demand. Comparisons between baseline and... | |
aeronautics/26303_119.txt | eropropulsive benefits of the SUSAN Electrofan’s DEP and BLI turbofan technologies. These aircraft models were developed through the application of gradient-based aerodynamic and aeropropulsive shape optimization capabilities based on Reynolds-averaged NavierStokes (RANS) computational fluid dynamics (CFD) and are show... | |
aeronautics/23855_20.txt | e and temperature, at the inflow [8–10] and static pressure at the outflow. Often, the outflow static pressurelevel is not known a priori or is not a primary parameter of the simulation.Often, the problem is driven by a required mass flow rate or Mach number atsome location in the flow. The desired result is still ulti... | |
aeronautics/12487_58.txt | y 0.46 mm thick, holding it in place can be an issue at high pressure drops. After several attempts, TIG welding the sample on a spacer ring yielded success, and the sample was able to stay secure throughout several cycles. The remaining case shown in Fig. 13 is an attempt to support the DP450661 with a thin, high poro... | |
aeronautics/00114_439.txt | -57779, pp, 20.1-20.25, June 1966.
13.Lyons, J. M. and Lum, A. J.: Ground Wind InducedOscillations of the Titan III ITL Transporter. NASATM-X-57779, 1966, pp. 5. 1-5.30. | |
aeronautics/00319_161.txt | f the wings, andas such do not suggest immediate application to largerscale, fixed wing flight. However, regions of unsteadyflow exist on most fixed wing aircraft during certainparts of the flight envelope. A prime example is thelanding approach of transport aircraft when the flapsand slats are deployed. The unsteady n... | |
aeronautics/14132_79.txt | m and downstream source.This was expected because the liner produces little attenuation at the anti-resonant frequency. Second, there is scatterin the educed normalized resistance near 2.5 kHz when the dual-source is used. This is due to the cut on of the nexthigher-order mode in the GFIT. This mode is not accounted fo... | |
aeronautics/14070_57.txt | n areshown in Fig. 4 up to the second derivative. The agreements are excellent.
Stability computations of TS instability waves are performed next by LASTRAC based on FUN3D andCFL3D solutions and by eMalik22 based on the similarity solution. The instability growth rates at twospatial locations, x = 0.945577 m and x = 1.... | |
aeronautics/23857_97.txt | N is the numberof nodes. Note that the experimental values are provided as dashed black linesfor reference. The results show that the FUN3D predicted IDCmax increases asthe grid refinement increases, while both the IDRmax and pressure recovery atthe AIP decrease with increasing grid refinement. Also, the trends show th... | |
aeronautics/26345_137.txt | s 𝑓𝑓𝑠𝑠 using the MELD transfer scheme. Subsequently, these forces are transferred to TACS for structural analysis, providing updated structural displacements 𝑢𝑢𝑠𝑠. These displacements are then transmitted back to the VLM solver in OpenAeroStruct using the MELD displacement transfer. Subsequently, the fluid mesh... | |
aeronautics/08613_14.txt | eahanisms hanisms MDAO CMDAO Cnt System ent System imum Imnimum Im
House House s sg Noise Generag Noise Generaabilities abilitiesilities ilitiesveloping a Mulveloping a Mulonent Analysis onent Analysis aand Technolog nd Technologies ies spects of Aircrapects of Aircrad Optimization
SA SA DiagDiagstand stand PrediPrediv... | |
aeronautics/25026_16.txt | . The definition of these anglesin the model coordinate system used throughout this paper are given in Fig.
The jet thrust coeffients in this test varied from 𝐶𝑇 ∈ [0.5, 2.5]. The CobraMRV was not placed on a balance tocompute the total thrust. Instead, the thrust was computed using the conditions in the jet plenum a... | |
aeronautics/22151_42.txt | r, Figure 6a). The yoke flap moment correlation is reasonable (Figure 7). The predicted lag moments capture the trends but not the magnitudes (Figures 8-9). The large twist of the 699 changes the orientation of the lag gages relative to the tip path plane, hence the inboard and outboard moments do not have the same tre... | |
aeronautics/20516_115.txt | , M., Witkowski, D., Watkins, A., Rivers, M., and Campbell, R., "Assessment of the National Transonic Facility for Natural Laminar Flow Testing", 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Aerospace Sciences Meetings, AIAA 2010-1302, January 2010. 16 Belisle, M.J., R... | |
aeronautics/19990_21.txt | t, and many interesting topics and problems that still need solving.
Next I would like to acknowledge my mentor and examiner at KTH, Per Wennhage, for giving me support and answering all my questions whenever needed, even though I was far away | |
aeronautics/13214_57.txt | 0 .
4. Results
4.1 ARX Model
Two ARX model orders were evaluated. Specifically, a model with order na = 5, nb = 1, nk = 1 and na = 10, nb = 1, nk = 1 were used for model development. The model order was estimated as discussed in section 2.2. This analysis allowed for us to assess whether adding complexity to the same s... | |
aeronautics/22950_34.txt | e would expect the integration results to accurately quantify the experimental noise sources up to at least this frequency.
The acoustic maps presented so far where obtained in narrowband using a frequency resolution of 50 Hz. If acoustic maps in 1/24th octave bands are generated from the narrowband maps, the relative ... | |
aeronautics/25101_39.txt | h tower CFD gridding and solutiondevelopment were described in Ref. [11]. Finally, Ref. [7] providedevidence from a recent 14-by 22-Foot Subsonic Wind Tunnel (14 × 22WT) test confirming the bistable nature of the flow through the gapsbetween the SRBs that was caused by the Coanda effect.
B. Computational Considerations... | |
aeronautics/09220_26.txt | = excitation frequencyt = reaction rail thicknessPr = resistivity of railge = electromagnetic airgap
The Goodness Factor (G) or the product ofslip x Goodness factor (σG) determines theultimate performance, power factor,efficiency peak thrust and optimumoperations slip values for each specificdesign.
Catapult type linea... | |
aeronautics/15913_57.txt | o safety incidents; prognostic algorithm design for safety assurance; and maintaining vehicle safety between major inspections. The digital twin method will provide a capability to predict and prevent safety issues by constantly monitoring usage and simulating possible future damage states. In addition to coping with w... | |
aeronautics/16608_86.txt | n of the slat cove shear layer (sensors S3 and S11 in Figs. 23(a) and 23(c), respectively), the NBPs are barely visible above the broadband spectrum at this chordwise location. However, the sensors away from the region of vortical fluctuations (sensors S10, S13, and M7 in Fig. 23(b), 23(d), and 23(e)), the NBPs are obs... | |
aeronautics/22291_53.txt |
A detailed description of how “3D Smooth” ice shapes weregenerated can be found in Camello, et al. [23,25] Details of “Max Scallop” ice shapes presented in this paper can be found in Woodard, et al. [14], and details of the “WB33” ice shapes can be found in Broeren, et al. [15] Page 6 of 19
Results and Discussions | |
aeronautics/13661_74.txt | d Shaqfeh, E. S., “Disturbance Evolution in a Mach 4.8 Boundary Layer with Two-Dimensional Roughness-Induced Separation and Shock,” J. Fluid Mech. (2010). Vol. 648, pp. 435-469. [15] Bountin, D., Chimitov, T., Maslov, A., Novikov, A., Egorov. I, and Fedorov, A | |
aeronautics/03485_115.txt | s laid out by the work package, they would not do it. This structure stymied integration. The bureaucracy of NASA was a real hindrance that prevented things that needed to be done from getting accomplished. The first project leader may outline the goals, then the next person who came in said, “We’re not doing it that w... | |
aeronautics/21149_34.txt | c heat ratio, µ is the dynamic viscosity and λ =23µ is the bulkviscosity.
We use a space-time discontinuous-Galerkin discretization of (1). We seek a solution u which satisfiesthe weak form
where the second and third integrals arise due to the spatial and temporal discontinuity, respectively, of thebasis functions. fdI... | |
aeronautics/23058_75.txt | ° while leaving other settings the same (now labeled Baseline G-III Aircraft – Aero Equivalent). The PNLT time histories for this configuration and the equivalent ACTE with flaps deflected 25 and porous MLG fairings installed are shown in Fig. 21. Observe that the flap and MLG NR concepts tested reduced PNLTmax by 4.2... | |
aeronautics/00847_71.txt | d order model to bermined and then a decision made about theessity of higher order terms
iterature search was performed to determine thee-of-the-art in third order designs. There was adestly large amount of literature describing thirder designs. However. the references in the literaturesix variable designs are a little... | |
aeronautics/06721_52.txt | o 30 min, indicating that this parameter should be varied during simulation testing ofautonomous soaring algorithms.
VII. Future Work
The updraft model presented in this paper is useful for the development of autonomous soaring guidance andcontrol but does not model all of the significant characteristics of naturally o... | |
aeronautics/12628_152.txt | 1992. 47. Deyhle, H., and Bippes, H., “Disturbance Growth in an unstable three-dimensional boundary layer and its dependence on environmental conditions,” J. Fluid Mech., Vol. 316, 1996, pp. 73-113. 48. Dougherty, N. S., and Fisher, D. F., “Boundary Layer Transition on a 10-deg Cone: Wind Tunnel/Flight Data Correlatio... | |
aeronautics/23313_334.txt | 1–5 April, pp. 249–256.Norman, D. (2013). The design of everyday things, Basic Books, New York.Rios, J. (2017). USS specification requirements, NASA Ames Research Center, working document, not for wide release. Rios, J. (2018). UTM TCL4 Statement of Work, NASA NASA Ames Research Center.Rios, J. (2019). UTM MOPS and MOE... | |
aeronautics/23299_51.txt | R of the Escort test points analyzed in the fan stator region are illustrated in Fig. 7. The symbols connected by dotted lines represent the values of Twbs at the full fan and at the fan-core RMS radii. The span wise work distribution in the fan rotor resulted in a gradient of static temperature, resulting in a large v... | |
aeronautics/23708_69.txt | , possibly due to differing tunnel humidity, and shows the importance of conducting an equilibration spray.
Further analysis is carried out without the BF spray (Figure 6(b)). Similar to Laforte et al. (Ref. 31), we show increasing grain sizes in the first few millimeters of the sample, with the grain size tending to l... | |
aeronautics/14559_304.txt | n flow and all of the Reynolds stresses, along with heat and mass-flux vectors, where applicable. These experimental data, along with available and/or future DNS, should be used to develop and evaluate second-order-closure models, as well as hybrid methods that are based on RANS and LES. Because turbulence models are n... | |
aeronautics/08716_64.txt | g that lead to the initiation of an international collaborative research effortknown as Vortex Flow Experiment 2. The baseline experimentation from NASA Langley showed significant effects of Mach number, Reynolds number, angle of attack, and leading-edge bluntness for the onset and progression ofleading-edge vortex sep... | |
aeronautics/09687_14.txt | tained by extrapolation using gradients computed at the mesh vertices using an unweighted least-squares technique.Limiting of the reconstructed values may be employed for flows with strong shocks. For all results presented in this paper, the convective flux scheme used is Roe’s flux difference splitting [4].For tetrahe... | |
aeronautics/17073_66.txt | d, altitude and heading of the intruder aircraft, and the predicted location of intercept with the TC. In particular: (i) UA heading outbound: If the predicted location of the intercept with the TC was in the forward path of the UA, then irrespective of whether the UA was in the northern or southern half of the TC, the... | |
aeronautics/14118_3.txt | . (21) Appl. No.: 11/603,664 (22) Filed: Nov. 22, 2006 (65) Prior Publication Data US 2008/0116010 Al May 22, 2008 (51) Int. Cl. F1 6H 57/04 (2010.01) FOLD 25118 (2006.01) (52) U.S. Cl. ........ 184/6.12; 184 | |
aeronautics/11346_39.txt |
represents vertical relative position, y lateral relative position,φ roll angle, and u longitudinal velocity. Vertical, lateral, andlongitudinal velocities; roll, pitch, and yaw angles; and roll,pitch, and yaw rates are contained in ξ. Elevator deflection isrepresented by δE, aileron deflection by δA, rudder deflectio... | |
aeronautics/05479_2.txt | (STI)Program Office plays a key part in helping NASAmaintain this important role.
The NASA STI Program Office is operated byLangley Research Center, the Lead Center forNASA’s scientific and technical information. TheNASA STI Program Office provides access to theNASA STI Database, the largest collection ofaeronautical ... | |
aeronautics/18718_3.txt | luating progress toward Outcomes. A few illustrative examples are also presented.
1.0 Introduction
The year 2015 marks the 100th anniversary of the founding of NASA’s predecessor, the National Advisory Committee for Aeronautics (NACA). Since that seminal event, aeronautics research has expanded from the fundamentals of... | |
aeronautics/14811_74.txt | e guidelines developed for the DPWand HiLiftPW. Mavriplis et al.28 summarize the grid-related lessons gleaned from the experiences of DPW.These guidelines remained relatively unchanged over the course of DPW II-IV and were maintained inthe HiLiftPW; the guidelines codify much of the collective experience of the applied... | |
aeronautics/16763_99.txt | .35) exit Mach number conditions were again evident (Fig. 25(b)). Conclusions
A new set of aerodynamic performance data was obtained for VSPT blading at engine relevant (high Tu) inlet turbulence conditions. The dataset complements an earlier dataset acquired at low inlet turbulence levels as required to achieve missi... | |
aeronautics/14034_48.txt | s rangedfrom about 0.74 × 106to 1.84 × 106). Rather it is an attemptto anchor the results in the context of historical data, andperhaps draw some qualitative comparisons.
Trajectory Simulation
Here, we present results of the DES simulations of the fourtrajectory points spanning the low supersonic to transonicregimes. A... |
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