Download or read book Supersonic Laminar Flow Control Research NASA CR 196260 1994 written by and published by . This book was released on with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Supersonic Laminar Flow Control Research written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-11-02 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of the research is to understand supersonic laminar flow stability, transition, and active control. Some prediction techniques will be developed or modified to analyze laminar flow stability. The effects of supersonic laminar flow with distributed heating and cooling on active control will be studied. The primary tasks of the research applying to the NASA/Ames Proof of Concept (POC) Supersonic Wind Tunnel and Laminar Flow Supersonic Wind Tunnel (LFSWT) nozzle design with laminar flow control are as follows: (1) predictions of supersonic laminar boundary layer stability and transition, (2) effects of wall heating and cooling for supersonic laminar flow control, and (3) performance evaluation of POC and LFSWT nozzles design with wall heating and cooling effects applying at different locations and various length. Lo, Ching F. Unspecified Center...

Download or read book NASA F 16xl Supersonic Laminar Flow Control Program Overview written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-12-28 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 ...

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 392 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Application of Laminar Flow Control to Supersonic Transport Configurations written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 192 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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...

Download or read book Supersonic Hlfc written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-11 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 ...

Download or read book Monthly Catalog of United States Government Publications written by and published by . This book was released on with total page 1450 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Three Dimensional Boundary Layer Program Bl3d for Swept Subsonic Or Supersonic Wings with Application to Laminar Flow Control written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-11-18 with total page 138 pages. Available in PDF, EPUB and Kindle. Book excerpt: The theory, formulation, and solution of three-dimensional, compressible attached laminar flows, applied to swept wings in subsonic or supersonic flow are discussed. Several new features and modifications to an earlier general procedure described in NASA CR 4269, Jan. 1990 are incorporated. Details of interfacing the boundary-layer computation with solution of the inviscid Euler equations are discussed. A description of the computer program, complete with user's manual and example cases, is also included. Comparison of solutions with Navier-Stokes computations with or without boundary-layer suction is given. Output of solution profiles and derivatives required in boundary-layer stability analysis is provided. Iyer, Venkit Unspecified Center BOUNDARY LAYER STABILITY; COMPRESSIBLE FLOW; COMPUTATIONAL FLUID DYNAMICS; INVISCID FLOW; LAMINAR BOUNDARY LAYER; SWEPT WINGS; THREE DIMENSIONAL FLOW; EULER EQUATIONS OF MOTION; NAVIER-STOKES EQUATION; SUBSONIC FLOW; SUPERSONIC FLOW; USER MANUALS (COMPUTER PROGRAMS)...

Download or read book Feasibility and Benefits of Laminar Flow Control on Supersonic Cruise Airplanes written by A. G. Powell and published by . This book was released on 1989 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Announcements Index written by and published by . This book was released on 1995 with total page 804 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Application of Laminar Flow Control Technology to Optimum Supersonic Cruise written by NORTHROP CORP HAWTHORNE CA NORAIR DIV. and published by . This book was released on 1965 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aeronautical Enginnering A Cumulative Index to a Continuing Bibliography supplement 312 written by and published by . This book was released on 1994 with total page 392 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Laminar Boundary Layer on a Circular Cone in Supersonic Flow at a Small Angle of Attack written by Franklin K. Moore and published by . This book was released on 1951 with total page 710 pages. Available in PDF, EPUB and Kindle. Book excerpt: The laminar boundary layer on a circular cone at angle of attack to a supersonic stream is discussed. A perturbation analysis was made to show the influence of a small angle of attack on such boundary layer quantities as skin friction, boundary-layer thickness, viscous lift, drag, and pitching moment.

Download or read book Laminar Flow Control written by Dal V. Maddalon and published by . This book was released on 1982 with total page 138 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Laminar Flow Control written by D.L. Key and published by . This book was released on 1982 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Numerical Solutions of the Navier Stokes Equations for the Supersonic Laminar Flow Over a Two dimensional Compression Corner written by James Edward Carter and published by . This book was released on 1972 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: Numerical solutions have been obtained for the supersonic, laminar flow over a two-dimensional compression corner. These solutions were obtained as steady-state solutions to the unsteady Navier-Stokes equations using the finite-difference method of Brailovskaya, which has the second-order accuracy in the spatial coordinates. Good agreement was obtained between the computed results and the wall pressure distributions measured experimentally by Lewis, Kubota, and Lees for Mach numbers of 4 and 6.06, and respective Reynolds numbers, based on free-stream conditions and the distance from the leading edge to the corner, of 6.8 x 104 and 1.5 x 105. In those calculations, as well as in others, sufficient resolution was obtained to show the streamline pattern in the separation bubble. Upstream boundary conditions to the compression-corner flow were provided by numerically solving the unsteady Navier-Stokes equations for the flat-plate flow field, beginning at the leading edge. The compression-corner flow field was enclosed by a computational boundary with the unknown boundary conditions supplied by extrapolation from internally computed points. Numerical tests were performed to deduce that the magnitude of the errors introduced by the extrapolation was small. Calculations were made to show the effect of ramp angle and wall suction on the interaction flow field. The pressure distributions obtained in the present calculations, including a case of incipient separation, were plotted together by using the free-interaction scaling of Stewartson and Williams. A good correlation of the numerical results was found, but only fair agreement was found between this correlation and the universal pressure distribution found numerically by Stewartson and Williams.

Download or read book Supersonic Flow Computations for an Astovl Aircraft Configuration Phase 2 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-12 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: A unified space/time marching method was used to solve the Euler and Reynolds-averaged Navier-Stokes equations for supersonic flow past an Advanced Short Take-off and Vertical Landing (ASTOVL) aircraft configuration. Lift and drag values obtained from the computations compare well with wind tunnel measurements. The entire calculation procedure is described starting from the geometry to final postprocessing for lift and drag. The intermediate steps include conversion from IGES to the patch specification needed for the CFD code, grid generation, and solution procedure. The calculations demonstrate the capability of the method used to accurately predict design parameters such as lift and drag for very complex aircraft configurations. Ramakrishnan, Sekaripuram V. and Chakravarthy, Sukumar R. and Szema, Kuo-Yen Unspecified Center NAS1-17492; RTOP 505-60-01-02...