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aeronautics/26298_73.txt | e required to best fit the experimental data is 50 hours, and the curves become linear.
We now investigate the effect of changing the diffusivity ratio while holding the boron arrival time fixed at 50 hours since this time appears to provide the best match with the experimental data. Figure 11 shows the result of incr... | |
aeronautics/23059_104.txt | , J.-R., Derlaga, J. M., Gnoffo, P. A., Hammond, D. P., Jones, W. T., Kleb, B., Lee-Rausch, E. M.,Nielsen, E. J., Park, M. A., Rumsey, C. L., Thomas, J. L., and Wood, W. A., “FUN3D Manual: 13.4,” NASA TM-2018-220096, | |
aeronautics/19333_88.txt | 2014-2481, 2014.9 Khorrami, M. R., Hannon, J. A., Neuhart, D. H., Markowski, G. A., and Van de Ven, T., “Aeroacoustic Studies of a High-Fidelity Aircraft Model: Part 1-Steady Aerodynamic Measurements,” AIAA Paper 2012-2233, 2012.10 Khorrami, M. R. and | |
aeronautics/15715_97.txt | sion for the actuator, the required orientation, and the volume of the actuator.
Based on the layout work, it was determined while challenges exist, particularly in the trailing edge bays where the rudder actuators reside, that no such major modifications were required. Had such changes been required, their impact on ... | |
aeronautics/07077_361.txt | wisted rotor.
Yeates (ref. 27) conducted flight tests of a tandemhelicopter. For descent with forward speed near zero, thefrequency was 1.0 to 1.5 Hz at Vz/vh ≅ –0.4; 0.7 to 0.8 Hzat Vz/vh ≅ –1.1. For descent with forward speed of 10knots (Vx/vh = 0.67), the frequency | |
aeronautics/17301_104.txt | n University, 1995. Thompson, G., R. M. Rasmussen, K. Manning, “Explicit Forecasts of Winter Precipitation using an Improved Bulk Microphysics Scheme. Part1: Description and Sensitivity Analysis”, Monthly Weather Review, Vol. 132, 2004, pp. 519-542. van der Geest, P., “Wake vortex severity criteria: The search for a si... | |
aeronautics/20380_41.txt | n defined previously, it is not necessary to approximate those shapes as ellipses or other primitive shapes. The elliptical method established how to “blend” the skirt shape to the maximum projection as a function of Z. It was therefore possible to blend the actual geometry between those horizontal planes to create an ... | |
aeronautics/13648_128.txt | 9, Reno, NV, January 2006.
Appendix
A. Comparison of Geometry Tools
Blender’s open-source status is highly advantageous in terms of cost and therefore scalability. Unlimitedinstances of the program can be active as geometry engines running in parallel, without facing the licenselimits typical of commercial software. Ne... | |
aeronautics/06770_98.txt | 5, 18.25, 26.875, 29.0, and 32.0 are shown in Figures 10, 11, 12, 13, 14, and 15, respectively. These six points in time were selected for later comparison with the published results of Goorjian.35 The top part (a) of each figure shows the surface pressure coefficient distribution and the bottom part (b) of each figure... | |
aeronautics/26175_3.txt | t to produce accurate and seamless regional monthly mean surface shortwave and longwave irradiances with time. Although a single sun-synchronous orbit introduces significant bias in surface irradiances for regions with strong cloud diurnal cycles, monthly regional surface anomalies align with those from two sun-synchro... | |
aeronautics/14779_36.txt | e. With
(P c – P ∞ ) / (q ∞ ) becomes
or
So, there is an error of ~2 percent at this Mach number just due to the fact that the pressures are measured at the surface of a 2⁰ cone. If one assumes a total pressure of 940 psf and a nominal static pressure of 120 psf in the equation forthis parameter at a Mach number in ter... | |
aeronautics/11967_45.txt | e 7 regarding the onset of buffet, pointing to flow separation occurring right over the Kulite location. The -182˚F runs show a larger Kulite peak compared to -250˚F and the reason for this is not clear. In summary, the Kulite rms pressure data from CRM tests shows that at M=0.7, the Kulite does not see flow separation... | |
aeronautics/23457_76.txt | e than half of a degree Celsius, which is within the measurement uncertainty of the temperature probes.
When the airflow velocity was increased to 185 m/s, there did not seem to be a noticeable change in temperature fluctuations with radial position as seen in Figure 13. This suggests that the turbulence intensity acr... | |
aeronautics/16682_95.txt | 0.275, a sweep angle of 35°, and a cruise Mach number of 0.85. For all flight loads a dynamic pressure of 5,897 Pa is used. The wing box is located between 12% and 71% of the local airfoil chord. The fixed weight of the aircraft is 500 kN, thus, in steady level flight, each wing must produce enough lift to support 250 ... | |
aeronautics/20237_204.txt | t shape that the thin shell will assume at maximum deflection after the impact is a very complex problem. We can get a rough estimate of the amount of bending energy in the shell by evaluating this energy for a deflection curve based on uniform pressure loading. We assume that this analysis gives us a curve of Mb = Mb(... | |
aeronautics/25360_45.txt | s greater than the maximum allowable temperature given in Table III are assigned baseline fitness values in the genetic algorithm. Due to the symmetry of the stator, only one half of one slot of the machine is used for the thermal model. Figure 5shows the geometry and layout of thermal resistances used. An in-slot cool... | |
aeronautics/20518_125.txt | sible boundary layers,” AIAA J., Vol. 41, 2003, pp. 2357–2363.29Zuccher, S., Tumin, A., and Reshotko, E., “Parabolic approach to optimal perturbations in compressible boundarylayers,” J. Fluid Mech., Vol. 556, 2006, pp. 189–216.30Paredes, P., Hanifi, A., Theofilis, V | |
aeronautics/14898_40.txt | (then quaternions) and accelerations to perform aninertial reconstruction of the capsule trajectory. The DIMU was installed to an angular accuracy of 1 milliradian abouteach axis relative to the descent stage. Through a stack-up of quality assurance (QA) measurements it was determinedthat the orientation knowledge of t... | |
aeronautics/08571_69.txt | d from the opposite side of the air vehicle. US 6,732,974 B1
7
The tiperon 3a, like the tiperon 3b, can be rotated about its control axis, as indicated by the arrows in FIG. 2, to control the air vehicle 1 in flight.
In operation, referring to FIGS. 1-3, the FCS 5 receives or generates the control signal and option... | |
aeronautics/10313_103.txt | , and tail are shown in Fig. 15, where the vertical scale has been exaggerated for clarity. The design procedure has increased the thickness of the wing and canard, as well as the camber across all three elements. Closer inspection shows that the trailing edges of each surface have also been deflected in a downward fas... | |
aeronautics/02850_51.txt | e 7.Figure 7 also shows the output of the decision fusion modelfor this experiment. Inspect was indicated early on in the test and shutdown was indicated at approximately reading2600. At test completion, it was found that damage alsooccurred on the pinion bearing. The damage is shown inFigure 8. Although the sensitivit... | |
aeronautics/17462_19.txt | nufacturing, and Test Development of a Composite Fan Blade Leading Edge Subcomponentfor Improved Impact Resistance
Sandi G. Miller, Katherine M. Handschuh, Matthew J. Sinnott, Lee W. Kohlman, Gary D. Roberts, Richard E. Martin, Charles R. Ruggeri, and J. Michael PereiraGlenn Research Center, Cleveland, Ohio Level of Re... | |
aeronautics/17916_69.txt | e. Further detail including include Bode and Nichols plots can be found inReference 3. B. FEM Based Control Law
FEM19 modes and unsteady doublet lattice aerodynamics were used to generate dynamic aeroelastic SSMs,which were used to develop control laws. Unsteady aerodynamics is represented by a P-transform methodin the... | |
aeronautics/15124_52.txt | nopy, resulting cient assumed tr the confluencin a higher drthe axial flow ce failure. Onerag coefficient,formulation, we would expect, but the compuwith results shot that the loss uted drag coefown in of the fficient The drag coefficient was also computed using the previously mentioned average off-axis angle of 3.18 ... | |
aeronautics/13731_53.txt | uency results of the TCA scaling andthe conversion of the analytical model to a buildable model. The designed buildable model frequencies wereroughly 5% higher than the scaled TCA frequencies, meaning the designed model was slightly stiffer orlighter than the scaled TCA.
III.C. Wing
The design of the outboard wing skin... | |
aeronautics/25229_31.txt | 1 psi) and the bottom row shows results for the highest flow rate (outflow pressure 14.11 psi); the left group of four images is was obtained with the SA turbulence model and the right group was obtained with the SA-RC-QCR turbulence model; finally, the left column in each group of four images is from the N050 grid, an... | |
aeronautics/06735_56.txt | , wasestablished downstream of the rapidly varying pressure gradients that occur as flow expands over the leading edge.This location was selected so that the desired scaled cavity with prescribed (H/δ, W/H, L/H) yielded reasonabledimensions in geometric space (H, W, L) for measurement resolution. Because of the uniquen... | |
aeronautics/14167_144.txt | e any significant effect on the results.
3.2.2 Approximating the Viscous Term
Here we discuss the approximation of the physical diffusion terms in the Navier-Stokes equationsby considering the derivative of the viscous flux function fv(ux) in Eq. (23). The derivative of theviscous flux function is defined by
where in g... | |
aeronautics/24702_90.txt | g. Other information that can be elucidated from the analyses include parameters like footprint area and footprint shape. Figure 15 illustrates differences in the footprint area with changes in the tire architecture; for example, the tire in Figure 15(a) is designed with a higher pitch, which can lead to a poorer footp... | |
aeronautics/23184_59.txt | [24, 25, 35], Görtler instability over a concave cone in a Mach 6 wind tunnel [36, 37], instability amplification over a distributed patch of roughness elements [38], and the boundary layer breakdown following the transient growth of traveling disturbances within the entropy layer over a blunt cone [39] | |
aeronautics/14393_88.txt | “Intelligence” ‐ make something complex enough and it “wakes up”. Presently Biomimmetics, nanosectioning the brain and replicating it in silicon, appears to be the foremost approach, with the IBM Blue Brain Project suggesting human level or nearly so machines at some 10‐15 years out. In the runup Machine Int | |
aeronautics/16637_49.txt | s with sizable deformations where the small angle approximations used in some traditional methods are no longer valid. The wing on the Boeing 787 (recall Figure 1) exhibits a sizable deformation of 10% semispan, for instance, and so a computational deformation scheme must properly capture the shape of this loaded wing.... | |
aeronautics/23008_32.txt | auralization. Refs. [6] and [15] provide additional details on FRAME.
Emission Angles: NAF Path Finder
The right side of the flowchart in Figure 3 shows the NAF Path Finder [14]. Its purpose is to generate tracking observer positions along the source hemisphere. Using flight path information, the Path Finder computes t... | |
aeronautics/19966_1.txt | Cooling Rate Study of Nickel-Rich MaterialDuring Thermal Treatment and Quench
Fransua ThomasGlenn Research Center, Cleveland, Ohio
Silvia Briseño MurguiaUniversity of North Texas, Denton, Texas Since its founding, NASA has been dedicated to the advancement of aeronautics and space science. The NASA Scientifi c and Tech... | |
aeronautics/10380_56.txt | y due to valve noise becomingprominent. Nevertheless, the agreement is excellent over the range 0.5<M;<1.2, exhibiting the occurrence of the excess noise in either facility. This should put to rest any doubt that the EBBN could be spuriousand facility dependent.
OASPL data corresponding to Figure 12 are shown in Figure... | |
aeronautics/09231_232.txt | nsport Configurations from the Second Drag-PredictionWorkshop,” Computers & Fluids, Vol. 34, 2005, pp. 785–816.56Wutzler, K., “Aircraft Drag Predictions Using COBALT,” AIAA Paper 2004-0395, January 2004.57May, G., van der Weide, E., Jameson, A., and Shankaran, S., “Drag Prediction of the DLR-F | |
aeronautics/23144_116.txt | upled yawing moment is carried by the flex beams and the T-section portion ofthe axial section. (For balances where the moment center lies at the center of the axialsection, the measurement beams do not carry any decoupled vertical load because theylie on the balance y − axis) The front and rear flex beam groups and th... | |
aeronautics/21210_22.txt | h, the work only partially examined the question of “settingthe proper boundary conditions.” Rogers et al. [6] also brought this issue upand developed a calibration formula to more closely align the conditions in theCFD with the conditions in the wind tunnel. In this paper, that concept iscarried one step further where... | |
aeronautics/19301_20.txt | eater is used. The facility operating mode is controlled by the position of a 24-ft valve.The test section elevation view is shown in figure 2. The upstream cross section of the testsection is 10 feet wide by 10 feet high. The test section is 40 feet long and its walls diverge 0o22’ to a width of 10.51 feet at the down... | |
aeronautics/24567_61.txt | seful whenevaluating SFCs developed outside the NASA SWS project.
B. Future Work
The authors intend to perform more extensive gap assessments for the SWS project, particularly regarding othertypes of use-cases that may be the subject of future demonstrations of the IASMS concept. The scope of this documentis to share t... | |
aeronautics/00893_9.txt | e RLV under development by KistlerAerospace Corporation is a fully reusable two-stage-to
orbit (TSTO) space transportation system. By rollingthe rift vector, each stage is steered to a landing pointthat is near the launch site 3. The first-stage, referred toas the launch assist platform (LAP), returns shortly afterlaun... | |
aeronautics/14123_85.txt | s (namely, radial and azimuthal directions in the present case). The final subsection (IV.D) considers the effects of nonlinear interactions within the leeward plane, albeit from the limited perspective of nonlinear PSE. 2. Effect of mean-flow non-parallelism on disturbance growth | |
aeronautics/00114_399.txt | A photograph ofthe 10% scale disk-gap-band parachute model is shown inFig. 121. The objeetivcs of the test were accomplished inthat large drag reductions measured for the originalconfiguration tested at AEDC wcrc verified, the designchanges produced considerable improvement in systemperformancc, and the new configurati... | |
aeronautics/21405_117.txt | 6 NASA PSL Transient Analysis
Of the four test runs in this series, only TR no. 139 (“b”) exhibited any ice growth in the first 20 s. For the first 9 s, no ice accreted on the airfoil, then ice accreted at a rate of 0.82 mm/s from 9 to 20 s, followed by ice growth at a steady-state beyond 20 s, at a rate of 0.26 mm/s | |
aeronautics/22799_57.txt | e surface areas of the sine and adjusted sine trailing edges as well as the asymmetric blade tip design.
Fig. 7C shows the comparison of the mechanical efficiency between each blade design. We are defining mechanicalefficiency as
where T is the thrust and P is the mechanical power and is determined by P = τω where τ is... | |
aeronautics/22925_65.txt | e 13. No attempt was made to model the cutoff frequencies and scale factors from observed statistics.
The effectiveness of the amplitude modulation model was assessed by reconstructing the original de-Dopplerized signal segment. Here the amplitude modulation data was provided by the model instead of from the signal dec... | |
aeronautics/07225_66.txt | r, those comparisons do not reveal the true uncertainties of using CFD for hypersonic aerodynamics prediction. A more important question that can be answered using the VL1 data is how well CFD methods would have predicted the trim α, CL, CD, and L/D. In the absence of modern computational tools, the pre-flight VL1 trim... | |
aeronautics/03103_47.txt | g Cl, Cm, Cn,and Cy for the free-flight model.
Vortex Calculations
The flight-measured vortex model was calculatedusing the following closed-form equations: 6' 7
Assuming the airplane is symmetriclongitudinal-vertical (X-Z) plane,about the
and the total moment equations simplify to | |
aeronautics/22649_157.txt | n/cdl/en/statug/63033/HTML/default/viewer.htm#mixed_toc.htm. [Accessed: 17-Sep-2018].[8] D. Bates, M. Mächler, B. Bolker, and S. Walker, “Fitting Linear Mixed-Effects Models using lme4,” ArXiv Prepr. ArXiv14065823, Jun. 2014.[9] “CRAN - Package nlme.” [Online]. Available | |
aeronautics/19872_115.txt | nnaud, R. M., Modena, M. C., Sanchez, E. V., “Lattice Boltzmann Method Contribution to the Second High-Lift Prediction Workshop,” AIAA Journal of Aircraft, Vol. 52, No. 4, 2015, pp. 1122–1135.[68] Mavriplis, D., Long, M., Lake, T., Langlois, M., “NSU3D Results for the | |
aeronautics/20055_65.txt | . The turbulent kinetic energy and Reynolds normal stresses show a similar behavior as the Reynoldsshear stress. Compared to the incompressible DNS of Schlatter and Orl¨u, ¨ 38 figure 7(a), v0v0 and w0w0 areunderpredicted in the range of 10 . y+ . 100, while u0u0 was overpredicted | |
aeronautics/06933_46.txt | k*-nullcline, given by:
and the u*-nullcline, given by:
The analytic form of the eigenvalues associated with this solution is very complicated, and does not yield a clear conclusion regarding the stability of the solution. However, it is easy to numerically find the eigenvalues for a point in the turbulent boundary l... | |
aeronautics/15717_95.txt | s of the tapered shape are necessary, as formation of tapered sections by hand is extremely difficult.
The two dental impression materials also have applications beyond the planned corner flow experiments, as the suitability for use in supersonic flow could allow them to be used to create other shapes, smooth out impe... | |
aeronautics/15586_66.txt | coping entropy flux relation (fully defined in section 3.2.2)is written as
and relates solution point data wi, wi+1, ψ˜i, ψ˜i+1 with a flux ¯filocated between the grid points.Conventional SBP operators are not directly applicable to this form of analysis; generalized operators suitable for a staggered grid implementati... | |
aeronautics/03666_94.txt | h as the appearance and disappearance of shock waves, vortices, and separated flow regions.
Coupling of Transonic Small Disturbance (TSD) potential flow methods, such as CAP-TSD, with interactive boundary layer schemes has proven to be effective in the prediction of LCO phenomena triggered by separation onset and shoc... | |
aeronautics/20955_17.txt | hms that includes software implementations as well asformal models for calculating containment and collision information for polygons. For example, PolyCARP can be used to determine whether a given point is inside or outside of aparticular polygonal region. In the Safeguard and ICAROUS systems, stay-in and stay-outregi... | |
aeronautics/23530_189.txt | o attempt was made to further subdivide the contributions (e.g., upper vs lower combustion zone). The results appear to show the contributions to the OASPL to be equally spread out over most of the combustion zone, somewhat similar to the N+3 approach results for the aft location.
In summary, the UHR field analysis sh... | |
aeronautics/25788_57.txt | s drop to idle (representing a failure), the commands diverge according to Equation (6). At 60 s, EE 2 “fails,” followed by 1 at 90 s. The remaining EE thrusts spread out, increasing on average, to maintain both total thrust and net torque on the aircraft, but no EEs saturate. At 120 s, EE 17 “fails,” followed by EE 16... | |
aeronautics/01009_16.txt | g and skin friction predictions, and the vehicle design raised concerns regarding the accuracy of turbulentflow prediction techniques. To address these concerns, a study to assess the accuracy of theturbulent heating and skin friction prediction techniques used to design the Hyper-X vehiclewas undertaken. This study co... | |
aeronautics/24038_59.txt | e 7. AoIs Neglect Latency by individual participant grouped by successful or unsuccessful outcome............................................................................................ 25
Table 1. Participant Flight Time ..... | |
aeronautics/25327_20.txt | flict . . . . . . . . . . . . . . . . . . . . . 7Figure 2.Inscribed and circumscribed elliptical intents to approximate the collision risk between rectangular intents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8Figure 3 | |
aeronautics/25742_26.txt | luesto be outputs of an augmentation function that belongs to a pre-determined function space (e.g.,a polynomial of a specified degree, a specific neural network architecture, etc.) and takes certainpre-determined model quantities as its inputs (features). | |
aeronautics/14329_18.txt | r of the core flowto the combustor module.
III.B.2. Combustor Module
The combustor module is composed of two parts, a hydrogen fuel injector and the hydrogen combustor, and is shown in Figure 4. The hydrogen fuel injector is fabricated from 321 stainless steel. Gaseous hydrogen fuel enters the injector from the center ... | |
aeronautics/05862_31.txt | e test section. The model was mounted on a 5-component balance to acquireforce and moment data. The model contains 832 pressure taps, however not all pressure taps were functioningduring the test. The pressure and balance data were acquired with no hot-films on the model. Five hundred hot-filmsensors were installed on ... | |
aeronautics/01400_6.txt | . The full-potential operator is of thetic type in the subsonic regime. Therefore. it, cantreated very elticimJtly by nmltigrid. In the suolfiC regime it becomes hyperbolic: wave equationh respect to the flow direction. For Mach mmfl)ertantially larger than one, the emire system cansolved efficiently by marching. Nearl... | |
aeronautics/03660_77.txt | g to trailing edge. The distance between the spinner and blade root is smaller than for the isolated configuration. The nacelle spinner rotates with the blades, sliding over a portion of the nacelle spinner collar.
INSTALLED ROTOR APPLICATION | |
aeronautics/22306_42.txt | s. The majority of the artificial ice shapes were manufactured from the Somos NeXt brand polymer. Some of the early ice shapes were rapid prototyped using Accura 60. The tolerances are advertised to be about +/- 0.005 inches for this process for either polymer. The Somos NeXt material was selected due to desirable adve... | |
aeronautics/09820_24.txt | quation is given formally in terms of integrals that describe convolution of the source distribution and propagation characteristics. Depending on the level of approximations involved in the description of the fan geometry and/or flow conditions, the solution can be expressed either in closed form or may require the us... | |
aeronautics/19660_131.txt | . 4, 1978, pp. 467–482.13Jiao, J., Delfs, J. W., and Dierke, J., “Towards CAA based Acoustic Wind Tunnel Corrections for Realistic Shear Layers,”AIAA 2015-3278, 21st AIAA/CEAS Aeroacoustics Conference, Dallas/Ft. Worth, TX, 2015.14Humphreys, W. M., | |
aeronautics/19412_16.txt | o the routine maintenance required on a powered modeland the increased number of personnel needed to operate the model. For example in the 14- by 22-Foot SubsonicTunnel (14x22) at NASA Langley Research Center (LaRC), it is not uncommon for a standard fixed-wing test to havea 50-70% wind-on rate compared to a powered ro... | |
aeronautics/21859_71.txt | tive to the static aeroelastic MLA result, the flutter constraint penalizes mass by 9.5%, andthe open-loop gust constraint by 20.4%. This is in strong contrast to the results without MLA included(upper portion of Fig. 5), where the flutter and gust constraints only add 1.4% and 3.6%, respectively. Onlyaeroelastic optim... | |
aeronautics/19412_41.txt | n. With a center point, the four-factor BBD contains twenty-five(25) unique runs. BBDs are also appealing because the factor settings are less extreme than those in a CCD becauseonly a subset of the factors are active. However, the BBD for the AFC test was slightly modified to eliminate factorcombinations not of intere... | |
aeronautics/19090_3.txt | A channels and by NASA in the NASA STI Report Series, which includes the following report types:
• TECHNICAL PUBLICATION. Reports of completed research or a major significant phase of research that present the results of NASA Programs and include extensive data or theoretical analysis. Includes compilations of signific... | |
aeronautics/25101_75.txt | 1.0.The third step employed an advancing front method to discretize theinviscid flow region. Finally, the POSTGRID utility was used to closeholes in the volume grid left by the VGRID process.
Further strategies for appropriately specifying the source strengthsand distributions were developed through a grid resolution s... | |
aeronautics/23550_571.txt | 2).O’Connor, P., Hörmann, H.-J., Flin, R., Lodge, M., Goeters, K.-M., & JARTEL Group, T. (2002). Developing a Method for Evaluating Crew Resource Management Skills: A European Perspective. The International Journal of Aviation Psychology, 12(3), 263–285. https://doi.org/10.1207/S15327108IJAP1203_5Reis, H. | |
aeronautics/23299_75.txt | g. Yet it was observed that ice accreted in the splitter-strut-shroud region.
A simple heat transfer model was created, where the initial unknown was the bulk heat transfer coefficient at the splittershroud flow path wall, hwall plenum. To estimate hwall plenum, two of the test data points were selected (156 and 283) w... | |
aeronautics/12033_18.txt | g the path of a given droplet from beginning of deformation to breakup and/or hitting the airfoil. Results are presented for droplets with a diameter of 490 micrometers at airfoil speeds of 50, 60, 70, 80 and 90 m/sec.
Nomenclature
avi = Audio video interleave movie format V = Velocity, mph Ttotal = Total temperature... | |
aeronautics/26388_361.txt | s for varying water inputs, and what regulatory changes might be necessary to implement widespread use of this technology?
Quantum Entangled Air Traffic Control
• Overview: Traditional air traffic management systems struggle with coordination and realtime decision-making, especially with increased air traffic. Voice co... | |
aeronautics/18498_25.txt | . The investigation focused on moderate (5) and high (8) bypass ratio exhausts.
Initial experiments by Henderson (Ref. 17) have shown the potential for noise reduction using a third stream under certain flow conditions. Papamoushco, Johnson and Phong (Ref. 18) have carried out experimental work to study the noise-redu... | |
aeronautics/20818_30.txt | . For the NTP-1 missions 11 round trip lander flights are needed for refueling. With NTP-2, the round trip lander flights needed are reduced to approximately 10. These numbers of flights do not include any additional hydrogen that may be required for cryogenic chill down of the stages tankage and other propulsion compo... | |
aeronautics/21751_131.txt | s-on simulations were performed with the model including cutout—whether the nose fan was included or not. Some grid refinements use automated body refinement (ABR) where RotCFD itself refines the grid based on the CAD model gradients between user-specified refinement limits.
The time-step related stability criterion mo... | |
aeronautics/10731_120.txt |
TC 2 exhibits similar behavior to the protuberance thermocouple. It reaches a laminarpeak relatively early in the trajectory and then steadily decreases before a rapid rise intemperature. The rapid rise in temperature is assumed to have been caused by transitionas a result of the BLT FE protuberance. The reference the... | |
aeronautics/11346_6.txt | rches to estimate the gradient andmove the system towards the extremum [11], [9].
The earliest work used classical-gradient methods partlydue to ease of implementation in analog devices and thelack of inexpensive digital computers. The classical-gradientmethods have recently been further developed in work byAriyur [12]... | |
aeronautics/14346_11.txt | l Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio 44135
Abstract
The effect of ice accretion on a 1/12-scale complete aircraft model of S-3B Viking was studied in a rotary-balance wind tunnel. Two types of ice accretions were considered: ice protection system failure shape and runback shape... | |
aeronautics/01943_58.txt | 10cruise, Dual-Fuel, Global-Reach (DFGR)vehicle t25].The original Hyper-X vehicle/enginekeel line corresponded to a photographicallyscaled version of the DFGR vehicle variablegeometry design at Mach 7 and 10, Because ofphysical scale and viscous and finite ratechemical kinetic effects IS1,changes to the engineflowpath... | |
aeronautics/23554_176.txt | yment process, improve the design,and predict the actual behavior in the space zero-g environment.
These simulations could be successfully achieved because of the presence of numerical damping in the transient solver. They show that the dynamic simulation of a tape spring can be made less sensitive to numerical parame... | |
aeronautics/16136_119.txt | e Meter Point Dynamic Planner (MPDP) in the architecture rather than having a single DP component.
3.1 Changes from a Software Metrics Perspective
It is often helpful to summarize significant software changes by using industry-standard software metrics. Approximately 15,900 lines of source code that were added to TBFM ... | |
aeronautics/20759_28.txt | s and documenting the encounter to the degree needed to extract useful information relative to the goals of this research. Some of those deficiencies include; non-constant icing conditions during the encounter, the inability to precisely measure the resulting ice shapes, and the fact that the impact of the ice accretio... | |
aeronautics/24055_190.txt | aileron and its mechanical actuators particularly under the added load from different actuation patterns.
Jet angle to local surface is investigated next in Figures 19 and 20. The jet angle is measured relative to the x coordinate, so in the previous actuation modes, the angle is 0°. Jet angles of +10° and -10° have ... | |
aeronautics/00932_111.txt | g positions, if necessary') where each engine position and orientation is accompaniedby a unique nozzle configuration.
Another way to reduce noise is to use many small engines instead of a few big ones.Small engines could be designed to have greater high-frequency noise content that wouldbe absorbed by the atmosphere. ... | |
aeronautics/23313_31.txt | 113.1.2 Requisite Properties Within UTM for USS-to-USS Negotiation .............................. 123.2 UTM Function: UVR Management........................................................... | |
aeronautics/05980_41.txt | 10 (e) at 0-degrees angle ofattack are presented in figure 11. The standard deviation for components A, B and Care less than 2 m/s rising at the extremes from model flare (near surface) to errorsfrom extrapolated optical alignment (127-mm extrapolation from the registrationtarget data). The conversion from DGV compone... | |
aeronautics/24180_328.txt | y and Commerce, House of Representatives Committee on Transportation and Infrastructure, August 20, 2020
21. Federal Communications Commission Working Group - Communication Strategies for Unmanned Aircraft Systems (UAS) – December 4, 2019
21. Federal Communications Commission Working Group - Communication Strategies f... | |
aeronautics/25795_187.txt | n Eq. (12), the ensemble average of the time rate of can be written as
re Ρ(∆, ⃗*,) is joint probability density function of the relative distance and velocit
Let ΖV⃗ = Ρ(∆, ⃗*,) (⃗* ∙ V⃗)⃗*, then Eq. (13) can be rewritten as | |
aeronautics/01009_37.txt | r and y+ for efficient and accurate turbulentheating and skin friction predictions.
4. Computational Procedure
Previous studies using this upwind, finite volume flow solver have demonstrated its ability toaccurately predict the flowfield on sharp cones[11], sharp nose hypersonic forebodies[12]and hypersonic forebody/in... | |
aeronautics/11360_29.txt | ealed in the same plot.
III. Rigid Steady Flow Results at Zero Angle of Attack
In the course of identifying the Mach number range of the bi-modal phenomenon, 13 baseline grid cases and 11fine grid cases were computed at Reynolds numbers along the Ares I-X nominal ascent trajectory in Table 1. To reducethe number of var... | |
aeronautics/00044_14.txt | f about12 ft. The approximate gross weight of the X-34 vehicleis 45000 lb. The main'wing of the X-34 vehicle has aleading edge sweepback of 45 °, a dihedral of 6°, and an80 ° leading edge strake and full span split elevons (fromactuator torque considerations). The elevons on the sameside are always deflected together. ... | |
aeronautics/20499_9.txt | e ARMD’s Spring 2016 announcement of a formal X-plane New Aviation Horizons Initative.1 Early task documentation encouraged an investigation of potential cost effective flight-test approaches to meet future ARMD flight research needs. Two near-term goals were also identified: 1) perform trade studies for vehicle config... | |
aeronautics/15013_103.txt | s, 3rd ed., 2006.17Tan, J. and Jin, J., “Stress Limiter Consideration for k−ω Turbulence Models in Shock Wave/Turbulent Boundary LayerInteractions in Supersonic and Hypersonic Flows ,” AIAA Paper 2011-3980, June 2011. 18Edwards, J. R., Choi, J. I., and Boles, J. A | |
aeronautics/17832_170.txt | epel away from the locale if the self-managing agent does not meet the requirements for adhesion. The adhere or repel signal can comprise information pertaining to requirements for adhesion and a locale for rendezvous purposes. The method can further comprise causing two or more of the self-managing agents that rendezv... |
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