04093cam a2200637Ia 4500011430752MiAaHDL20141013010000.0m d cr bn ---auaua060605s1979 dcua bt f000 0 eng d820699819790022977N793114879N3114819790023992N793216379N32163sdr-uiuc6384677(OCoLC)69861360FERFERGPOUIUU830-H-14 (microfiche)NAS 1.26:2849D6-44459D6-44458Richard, M.A program to compute three-dimensional subsonic unsteady aerodynamic characteristics using the doublet lattice method, L216 (DUBFLEX) /M. Richard and B.A. Harrison.Washington, D.C. :National Aeronautics and Space Administration ;Springfield, Va. :For sale by the National Technical Information Service [distributor],1979.2 v. :ill. ;27 cm.NASA contractor report ;2849-2850"NASA CR-2849"--V. I report documentation page; "NASA CR-2850"--V. II report documentation page.Performing organization report numbers: D6-44458 and D6-44459."October 1979"--V. I cover; "September 1979"--V. II cover.Includes bibliographical references.v. I. Engineering and usage. -- v. II. Supplemental system design and maintenance document.The program input presented consists of configuration geometry, aerodynamic parameters, and modal data; output includes element geometry, pressure difference distributions, integrated aerodynamic coefficients, stability derivatives, generalized aerodynamic forces, and aerodynamic influence coefficient matrices. Optionally, modal data may be input on magnetic file (tape or disk), and certain geometric and aerodynamic output may be saved for subsequent use.--V. I. The information necessary for execution of the digital computer program L216 on the CDC 6600 is described. L216 characteristics are based on the doublet lattice method. Arbitrary aerodynamic configurations may be represented with combinations of nonplanar lifting surfaces composed of finite constant pressure panel elements, and axially summetric slender bodies composed of constant pressure line elements. Program input consists of configuration geometry, aerodynamic parameters, and modal data; output includes element geometry, pressure difference distributions, integrated aerodynamic coefficients, stability derivatives, generalized aerodynamic forces, and aerodynamic influence coefficient matrices. Optionally, modal data may be input on magnetic field (tape or disk), and certain geometric and aerodynamic output may be saved for subsequent use.--V. II.Also available online from the NASA Technical Reports Server (http://ntrs.nasa.gov/).Performed by Boeing Commercial Airplane Company, Seattle, Washington for Langley Research CenterNAS 1-13918Mode of access: Internet.Aerodynamics.Lifting bodies.nasatFlow charts.nasatCDC 6600 computer.nasatSlender bodies.nasatLift devices.nasatLattices (mathematics).nasatInput/output routines.nasatUser manuals (computer programs).nasatUnsteady flow.nasatSystems engineering.nasatSubsonic speed.nasatComputer programs.nasatAerodynamic characteristics.nasatHarrison, B. A.Langley Research Center.Boeing Commercial Airplane Company.01143075220101026102613.020141013010000.020141112173021.02025-01-01T19:19:05Z2025-01-01T18:30:02ZSDR-UIUCUNKNOWNloader.pl-003-020BKsdr-uiuc6384677uiugSDRUIUCuiug.30112106583096UIUv.26384677UIUUIUC20250101googleuiug.30112106583096v.21979pdbibUS fed doc--NTIS: pubdate < 2020UIUUIUC20250101googleuiug.30112106583104v.11979pdbibUS fed doc--NTIS: pubdate < 2020