A program to compute three-dimensional subsonic unsteady aerodynamic characteristics using the doublet lattice method, L216 (DUBFLEX)

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086 0 ⊔ ‡aNAS 1.26:2849
088 ⊔ ⊔ ‡aD6-44459
088 ⊔ ⊔ ‡aD6-44458
100 1 ⊔ ‡aRichard, M.
245 1 2 ‡aA program to compute three-dimensional subsonic unsteady aerodynamic characteristics using the doublet lattice method, L216 (DUBFLEX) / ‡cM. Richard and B.A. Harrison.
260 ⊔ ⊔ ‡aWashington, D.C. : ‡bNational Aeronautics and Space Administration ; ‡aSpringfield, Va. : ‡bFor sale by the National Technical Information Service [distributor], ‡c1979.
300 ⊔ ⊔ ‡a2 v. : ‡bill. ; ‡c27 cm.
490 ⊔ 0 ‡aNASA contractor report ; ‡v2849-2850
500 ⊔ ⊔ ‡a"NASA CR-2849"--V. I report documentation page; "NASA CR-2850"--V. II report documentation page.
500 ⊔ ⊔ ‡aPerforming organization report numbers: D6-44458 and D6-44459.
500 ⊔ ⊔ ‡a"October 1979"--V. I cover; "September 1979"--V. II cover.
504 ⊔ ⊔ ‡aIncludes bibliographical references.
505 0 ⊔ ‡av. I. Engineering and usage. -- v. II. Supplemental system design and maintenance document.
520 ⊔ ⊔ ‡aThe 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.
530 ⊔ ⊔ ‡aAlso available online from the NASA Technical Reports Server (http://ntrs.nasa.gov/).
536 ⊔ ⊔ ‡aPerformed by Boeing Commercial Airplane Company, Seattle, Washington for Langley Research Center ‡bNAS 1-13918
538 ⊔ ⊔ ‡aMode of access: Internet.
650 ⊔ 0 ‡aAerodynamics.
650 ⊔ 7 ‡aLifting bodies. ‡2nasat
650 ⊔ 7 ‡aFlow charts. ‡2nasat
650 ⊔ 7 ‡aCDC 6600 computer. ‡2nasat
650 ⊔ 7 ‡aSlender bodies. ‡2nasat
650 ⊔ 7 ‡aLift devices. ‡2nasat
650 ⊔ 7 ‡aLattices (mathematics). ‡2nasat
650 ⊔ 7 ‡aInput/output routines. ‡2nasat
650 ⊔ 7 ‡aUser manuals (computer programs). ‡2nasat
650 ⊔ 7 ‡aUnsteady flow. ‡2nasat
650 ⊔ 7 ‡aSystems engineering. ‡2nasat
650 ⊔ 7 ‡aSubsonic speed. ‡2nasat
650 ⊔ 7 ‡aComputer programs. ‡2nasat
650 ⊔ 7 ‡aAerodynamic characteristics. ‡2nasat
700 1 ⊔ ‡aHarrison, B. A.
710 2 ⊔ ‡aLangley Research Center.
710 2 ⊔ ‡aBoeing Commercial Airplane Company.
CID ⊔ ⊔ ‡a011430752
DAT 0 ⊔ ‡a20101026102613.0 ‡b20141013010000.0
DAT 1 ⊔ ‡a20141112173021.0 ‡b2025-01-01T19:19:05Z
DAT 2 ⊔ ‡a2025-01-01T18:30:02Z
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