Design for minimum fuselage drag

Roskam, J.; Fillman, G. L.

doi:10.2514/3.44550

Cited by 7 publications

(6 citation statements)

References 3 publications

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“…Therefore, the many functions of aeronautical structural components must be considered before the design stage in to satisfactory to all the requirements of airlines. However, some of these functions mentioned determine the importance of required properties and their relation to different loading rates, as shown in Figure 1 [ 24 ]. One of the most important aeronautical structural components is the cockpit.…”

Section: Introductionmentioning

confidence: 99%

Synthesis and Characterization of Hybrid Fiber-Reinforced Polymer by Adding Ceramic Nanoparticles for Aeronautical Structural Applications

et al. 2021

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The multiscale hybridization of ceramic nanoparticles incorporated into polymer matrices reinforced with hybrid fibers offers a new opportunity to develop high-performance, multifunctional composites, especially for applications in aeronautical structures. In this study, two different kinds of hybrid fibers were selected, woven carbon and glass fiber, while two different ceramic nanoparticles, alumina (Al2O3) and graphene nanoplatelets (GNPs), were chosen to incorporate into a polymer matrix (epoxy resin). To obtain good dispersion of additive nanoparticles within the resin matrix, the ultrasonication technique was implemented. The microstructure, XRD patterns, hardness, and tensile properties of the fabricated composites were investigated here. Microstructural characterization demonstrated a good dispersion of ceramic nanoparticles of Al2O3 and GNPs in the fabricated composites. The addition of GNPs/Al2O3 nanoparticles as additive reinforcements to the fiber-reinforced polymers (FRPs) induced a significant increase in the hardness and tensile strength. Generally, the FRPs with 3 wt.% nano-Al2O3 enhanced composites exhibit higher tensile strength as compared with all other sets of composites. Particularly, the tensile strength was improved from 133 MPa in the unreinforced specimen to 230 MPa in the reinforced specimen with 3 wt.% Al2O3. This can be attributed to the better distribution of nanoparticles in the resin polymer, which, in turn, induces proper stress transfer from the matrix to the fiber phase. The hybrid mode mechanism depends on the interaction among the mechanical properties of fiber, the physical and chemical evolution of resin, the bonding properties of the fiber/resin interface, and the service environment. Therefore, the hybrid mode of woven carbon and glass fibers at a volume fraction of 64% with additive nanoparticles of GNPs/Al2O3 within the resin was appropriate to produce aeronautical structures with extraordinary properties.

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Section: Introductionmentioning

confidence: 99%

Synthesis and Characterization of Hybrid Fiber-Reinforced Polymer by Adding Ceramic Nanoparticles for Aeronautical Structural Applications

et al. 2021

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“…Welborn et al (41) provided experimental results for the distortion coefficients in S-shaped ducts, and Zhang et al (42) used a fine grid to achieve good agreement with the reported values using an algebraic turbulence model. An investigation performed by Smith et al (33) found good agreement between experimental data and results computed using an algebraic turbulence model. In order to determine the optimum turbulence model for this class of flows, previous work on diffusers will be relied upon.…”

Section: Previous Computational Techniques Have Been Used To Model Dumentioning

confidence: 95%

“…Recent works (22,37) performed sensitivity studies on diffusers using different turbulent models and concluded that either the Spalart-Allmaras (SA, with rotation corrections) or the SST using k-ω two equation model be used. This approach was used previously for the design of a S-duct inlet (33,41) . Figure 38 shows the results on the total pressure recovery (PR) and the flow distortion index (DC60) at several geometric combinations for the S-duct study.…”

Section: Previous Computational Techniques Have Been Used To Model Dumentioning

confidence: 99%

Inlet Shape Considerations For Split-Wing Electric Distributed Propulsion

Papathakis¹

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This thesis aims to uncover preliminary design relationships for an inlet of a split-wing electric distributed propulsion regional airliner. Several aspects of the inlet design were investigated, including: the overall thickness of the airfoil section with respect to the chord, inlet throat area, and lip radius. These parameters were investigated using several angles of attack and mass flow rates through the fan.Computational fluid dynamics, with a 2 nd Order turbulence model was used and validated against World War II era data from NACA, as those studies were the most pertinent wind tunnel data available.

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“…The SSL values can be seen in Table 3. Actual test temperatures fluctuated between 56 to 61° F, a density around 0.00235 slugs/ft 3 , and a pressure around 14.72psi. …”

Section: Operating Conditionsmentioning

confidence: 99%

“…(3) If that drag can be reduce by 50%, there would be an overall vehicle drag reduction of 15-25%. This would be a huge finding, as current commercial wing and tube designs typically find single percent point decreases in drag as a great increase in drag reduction.…”

Section: Motivationmentioning

confidence: 99%

Analysis of a Goldschmied Propulsor Using Computational Fluid Dynamics Referencing California Polytechnic’s Goldschmied Propulsor Testing

Seubert¹

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The Goldschmied Propulsor is a concept that was introduced in mid 1950's by Fabio Goldschmied. The concept combines boundary layer suction and boundary layer ingestion technologies to reduce drag and increase propulsor efficiency. The most recent testing, done in 1982, left questions concerning the validity of the results. To answer these questions a 38.5in Goldschmied Propulsor was constructed and tested in Cal Poly's 3x4ft wind tunnel. The focus of their wind tunnel investigation was to replicate Goldschmied's original testing and increase the knowledge base on the subject. The goal of this research was to create a computational fluid dynamics (CFD) model to help visualize the flow phenomenon and see how well CFD was able to replicate Cal Poly's wind tunnel results. CFD cases were run to get a comparison of the computational model and the wind tunnel results. For the straight tunnel geometry for the 0.385" slot and cusp A we found a body, pressure and friction drag, fan off C D of 0.0526 and a fan on at 500 Pascals with a C D of 0.0545. This is similar to the wind tunnel results but because of large errors in measuring overall drag we are not able to directly compare to the wind tunnel results. Overall we see that the trends match, mainly that the fan does not decrease the total pressure drag. This was a result of poor geometry and high fan speeds needed for attachment. The tested geometry is less than ideal and has a long way to go before it is of a shape that would have the potential to reduce the pressure drag as much as Goldschmied claimed. Future efforts should be put forth optimizing the aft body to reduce the low pressure in front of the slot and improving aft entrance of the slot to allow for a smoother flow.v ACKNOWLEDGMENTS

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Design for minimum fuselage drag

Cited by 7 publications

References 3 publications

Synthesis and Characterization of Hybrid Fiber-Reinforced Polymer by Adding Ceramic Nanoparticles for Aeronautical Structural Applications

Synthesis and Characterization of Hybrid Fiber-Reinforced Polymer by Adding Ceramic Nanoparticles for Aeronautical Structural Applications

Inlet Shape Considerations For Split-Wing Electric Distributed Propulsion

Analysis of a Goldschmied Propulsor Using Computational Fluid Dynamics Referencing California Polytechnic’s Goldschmied Propulsor Testing

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