Application Of Laminar Flow Control To Supersonic Transport Configurations
Download Application Of Laminar Flow Control To Supersonic Transport Configurations full books in PDF, epub, and Kindle. Read online free Application Of Laminar Flow Control To Supersonic Transport Configurations ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 192 |
| Release | : 2018-07-17 |
| Genre | : |
| ISBN | : 9781722947576 |
The feasibility and impact of implementing a laminar flow control system on a supersonic transport configuration were investigated. A hybrid laminar flow control scheme consisting of suction controlled and natural laminar flow was developed for a double-delta type wing planform. The required suction flow rates were determined from boundary layer stability analyses using representative wing pressure distributions. A preliminary design of structural modifications needed to accommodate suction through a perforated titanium skin was carried out together with the ducting and systems needed to collect, compress and discharge the suction air. The benefits of reduced aerodynamic drag were weighed against the weight, volume and power requirement penalties of suction system installation in a mission performance and sizing program to assess the net benefits. The study showed a feasibility of achieving significant laminarization of the wing surface by use of a hybrid scheme, leading to an 8.2 percent reduction in the cruise drag. This resulted in an 8.5 percent reduction in the maximum takeoff weight and a 12 percent reduction in the fuel burn after the inclusion of the LFC system installation penalties. Several research needs were identified for a resolution of aerodynamics, structural and systems issues before these potential benefits could be realized in a practical system. Parikh, P. G. and Nagel, A. L. Unspecified Center AERODYNAMIC DRAG; BOUNDARY LAYER CONTROL; BOUNDARY LAYER STABILITY; LAMINAR BOUNDARY LAYER; PRESSURE DISTRIBUTION; SUPERSONIC TRANSPORTS; WING PLANFORMS; WINGS; AERODYNAMICS; DRAG REDUCTION; FLOW VELOCITY; LAMINAR FLOW; SUCTION; TAKEOFF; TITANIUM...
| Author | : NORTHROP CORP HAWTHORNE CA NORAIR DIV. |
| Publisher | : |
| Total Pages | : 21 |
| Release | : 1965 |
| Genre | : |
| ISBN | : |
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 48 |
| Release | : 2018-07-11 |
| Genre | : |
| ISBN | : 9781722830083 |
The viewgraphs and discussion of the potential benefits and technology development requirements of supersonic Hybrid Laminar Flow Control (HLFC) are reviewed. For the last three years, Boeing has performed studies on the application of laminar flow control to High Speed Civil Transport (HSCT) configurations. Large potential net benefits were identified for laminar flow control, even after accounting for the significant implementation penalties. However, the technical risks are high at this time, and an early, aggressive technology development program is required if laminar flow control (LFC) is to be incorporated in a year 2005 HSCT program. The benefits and required development effort are addressed. Of all the aerodynamic advances that are being considered for the HSCT, LFC has the largest potential for improving the supersonic lift drag ratio of a given configuration. The work accomplished to date, sponsored by NASA Langley, is summarized. This work includes studies on HLFC application to HSCT, cruise HLFC/low speed boundary layer control (BLC) compatibility, and impact of M 0.9 HLFC and high lift BLC. Requirements for production committments are listed. The need for a HSCT-HLFC Risk Reduction Program is addressed. Supersonic HLFC development planning and future applications are addressed. Laminar flow/high-lift integration is addressed. Neumann, Frank Unspecified Center ...
| Author | : |
| Publisher | : |
| Total Pages | : 136 |
| Release | : 1989 |
| Genre | : |
| ISBN | : |
| Author | : Albert L. Braslow |
| Publisher | : |
| Total Pages | : 94 |
| Release | : 1999 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : Albert L. Braslow |
| Publisher | : |
| Total Pages | : 90 |
| Release | : 1999 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : National Aeronautics and Space Adm Nasa |
| Publisher | : Independently Published |
| Total Pages | : 26 |
| Release | : 2018-12-28 |
| Genre | : |
| ISBN | : 9781792696619 |
The viewgraphs and discussion of the NASA supersonic laminar flow control program are provided. Successful application of laminar flow control to a High Speed Civil Transport (HSCT) offers significant benefits in reductions of take-off gross weight, mission fuel burn, cruise drag, structural temperatures, engine size, emissions, and sonic boom. The ultimate economic success of the proposed HSCT may depend on the successful adaption of laminar flow control, which offers the single most significant potential improvements in lift drag ratio (L/D) of all the aerodynamic technologies under consideration. The F-16XL Supersonic Laminar Flow Control (SLFC) Experiment was conceived based on the encouraging results of in-house and NASA supported industry studies to determine if laminar flow control is feasible for the HSCT. The primary objective is to achieve extensive laminar flow (50-60 percent chord) on a highly swept supersonic wing. Data obtained from the flight test will be used to validate existing Euler and Navier Stokes aerodynamic codes and transition prediction boundary layer stability codes. These validated codes and developed design methodology will be delivered to industry for their use in designing supersonic laminar flow control wings. Results from this experiment will establish preliminary suction system design criteria enabling industry to better size the suction system and develop improved estimates of system weight, fuel volume loss due to wing ducting, turbocompressor power requirements, etc. so that benefits and penalties can be more accurately assessed. Fischer, Michael C. Langley Research Center ...
| Author | : |
| Publisher | : |
| Total Pages | : 260 |
| Release | : 1992 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 70 |
| Release | : 1976 |
| Genre | : |
| ISBN | : |
| Author | : Laurie A. Marshall |
| Publisher | : |
| Total Pages | : 58 |
| Release | : 1999 |
| Genre | : Boundary layer |
| ISBN | : |
A variable-porosity suction glove has been flown on the F-16XL-2 aircraft to demonstrate the feasibility of this technology for the proposed High-Speed Civil Transport (HSCT). Boundary-layer transition data have been obtained on the titanium glove primarily at Mach 2.0 and altitudes of 53,000-55,000 ft. The objectives of this supersonic laminar flow control flight experiment have been to achieve 50- to 60-percent-chord laminar flow on a highly swept wing at supersonic speeds and to provide data to validate codes and suction design. The most successful laminar flow results have not been obtained at the glove design point (Mach 1.9 at an altitude of 50,000 ft). At Mach 2.0 and an altitude of 53,000 ft, which corresponds to a Reynolds number of 22.7 multiplied by 10[factor 6], optimum suction levels have allowed long runs of a minimum of 46-percent-chord laminar flow to be achieved. This paper discusses research variables that directly impact the ability to obtain laminar flow and techniques to correct for these variables.
