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| 008 | 210309s1980 ohua bt f000 0 eng d | ||
| 035 | ⊔ | ⊔ | ‡a(MiU)99187886904906381 |
| 035 | ⊔ | ⊔ | ‡asdr-miu.99187886904906381 |
| 035 | ⊔ | ⊔ | ‡a(OCoLC)1240821037 |
| 035 | ⊔ | ⊔ | ‡a(GWLA)gwla on1240821037 |
| 040 | ⊔ | ⊔ | ‡aTRAAL ‡beng ‡cTRAAL |
| 049 | ⊔ | ⊔ | ‡aMAIN |
| 086 | 0 | ⊔ | ‡aD 301.45/46-2: 79-3138 Volume II |
| 100 | 1 | ⊔ | ‡aKnight, Doyle D., ‡eauthor. |
| 245 | 1 | 0 | ‡aCalculation of high speed inlet flows using the Navier-Stokes equations. ‡nVolume II, ‡pUser's and programmer's guide / ‡cDoyle D. Knight. |
| 264 | ⊔ | 1 | ‡aWright-Patterson Air Force Base, Ohio : ‡bAir Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, ‡c1980. |
| 300 | ⊔ | ⊔ | ‡aviii,129 pages : ‡billustrations, figures, tables ; ‡c28 cm. |
| 336 | ⊔ | ⊔ | ‡atext ‡btxt ‡2rdacontent |
| 337 | ⊔ | ⊔ | ‡aunmediated ‡bn ‡2rdamedia |
| 338 | ⊔ | ⊔ | ‡avolume ‡bnc ‡2rdacarrier |
| 490 | 0 | ⊔ | ‡aAir Force Flight Dynamics Laboratory (U.S.). Technical Report ; ‡vAFFDL-TR-79-3138 Volume II |
| 500 | ⊔ | ⊔ | ‡a"This report was prepared by the Department of Mechanical, Industrial and Aerospace Engineering, Rutgers University, New Brunswick, New Jersey." |
| 500 | ⊔ | ⊔ | ‡a"Final Report for period April 1978-September 1979." |
| 500 | ⊔ | ⊔ | ‡a"February 1980." |
| 504 | ⊔ | ⊔ | ‡aIncludes bibliographic references (pages 104-106). |
| 520 | ⊔ | ⊔ | ‡aA set of computer programs has been developed to calculate the flowfield in two-dimensional mixed-compression high speed inlets. The full mean compressible Navier-Stokes equations are utilized, with turbulence represented by an algebraic eddy viscosity model which incorporates a relaxation correction. A curvilinear body-oriented coordinate system is employed to allow handling of arbitrary inlet contours. Boundary layer bleed is incorporated. The numerical algorithm of MacCormack is employed to solve the Navier-Stokes equations. A variety of techniques are incorporated to improve code efficiency, including time-splitting of the finite-difference operators, automatic mesh-splitting, and a separate algorithm for the treatment of the viscous sublayer portion of the turbulent boundary layers. The numerical codes have been successfully applied to the calculation of a variety of flows including shock-boundary layer interaction on a flat plate (including both unseparated and separated cases), and three different simulated high speed inlet configurations. In all cases, good agreement was obtained with the experimental data. |
| 536 | ⊔ | ⊔ | ‡aAir Force Contract No. ‡bF33615-78-C-3008, Program Element 61102F, Work Unit No. 2307N415. |
| 538 | ⊔ | ⊔ | ‡aMode of access: Internet. |
| 650 | ⊔ | 0 | ‡aTurbulent boundary layer. |
| 650 | ⊔ | 0 | ‡aNavier-Stokes equations. |
| 650 | ⊔ | 0 | ‡aAirplanes ‡xRamjet engines ‡xAir intakes. |
| 710 | 2 | ⊔ | ‡aAir Force Flight Dynamics Laboratory (U.S.). ‡eissuing body. |
| 710 | 2 | ⊔ | ‡aAir Force Wright Aeronautical Laboratories. ‡esponsor. |
| 710 | 2 | ⊔ | ‡aRutgers University. ‡bDepartment of Mechanical & Aerospace Engineering, ‡esponsor. |
| 730 | 0 | ⊔ | ‡aTechnical Report Archive & Image Library (TRAIL) |
| 899 | ⊔ | ⊔ | ‡a39015095334598 |
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| 974 | ⊔ | ⊔ | ‡bMIU ‡cGWLA ‡d20240702 ‡sgoogle ‡umdp.39015095334598 ‡y1980 ‡rpd ‡qbib ‡tUS fed doc |