Test description and preliminary pitot-pressure surveys for Langley Test Technique Demonstrator at Mach 6

Everhart, Joel L.; Ashby, G. C.; Monta, W. J.

doi:10.2514/6.1992-3940

Cited by 2 publications

(2 citation statements)

References 3 publications

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“…The TTD is a generic SSTO configuration which has been the subject of numerous experimental and computational studies involving simulation of powered scramjet exhaust flow fields. [2][3][4][5][6][7][8][9][10][11][12] Sketches of the TTD geometry are shown in figure 1. The full-scale TTD configuration is 42.672 meters (1680 inches) in length with a wing span of 10.16 meters (400 inches).…”

Section: Configuration Geometrymentioning

confidence: 99%

Enhanced control effector designs for airbreathing transatmospheric vehicles

Cockrell

Mcminn

1997

35th Aerospace Sciences Meeting and Exhibit

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A study was conducted to evaluate the potential effectiveness of a moveable cowl-trailing-edge design for airbreathing hypersonic single-stage-to-orbit (SSTO) configurations, which can be extended or deflected from the nominal position in order to provide additional pitching moment capability. This additional pitching moment capability may reduce the necessary deflection angle from conventional control surfaces and the associated trim drag penalty. Calculations for a generic SSTO configuration with baseline and modified cowl trailing edge geometries were performed at Mach 6 and 10 initially with an engineering analysis code in order to examine several design parametrics. In order to more accurately model geometries and flow physics, 2-D viscous computational fluid dynamics (CFD) predictions were obtained. FInally, a limited set of 3D CFD predictions were obtained at Mach 6 in order to show the effects of modeling 3D flow fields as well as the full 3D vehicle geometry. Comparisons of aftbody surface pressures and force and moment predictions show differences between initial predictions and 2-D CFD solutions due to geometry modeling and calculation method differences. The 3-D CFD predictions confirm the trends observed in the 2-D solutions and provide additional information on 3D effects. These analyses shows that cowltrailing-edge extensions were effective in providing additional (nose-down) pitching moment increments as well as increased thrust compared to the baseline geometry. These effects reduce the control surface deflection angle required to trim the vehicle and the associated trim drag. Cowl-trailingedge deflections were not as effective, generating more noseup pitching moment and decreased thrust compared to nondeflected cases.

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Section: Configuration Geometrymentioning

confidence: 99%

Enhanced control effector designs for airbreathing transatmospheric vehicles

Cockrell

Mcminn

1997

35th Aerospace Sciences Meeting and Exhibit

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“…Two small scale models (approximately 1.5 and 3 feet long) have been fabricated for scramjet exhaust simulation powered testing in NASA Langley's highspeed wind tunnels 8, 9 . Reference 8 describes methodology for using metric model parts to obtain force and moment data under powered conditions, and reference 9 describes the acquisition of powered effects data using surface and flow field pressure measurements.…”

Section: Model Geometrymentioning

confidence: 99%

Exhaust gas modeling effects on hypersonic powered simulation at Mach 10

Kenneth¹,

Lawrence²

1995

International Aerospace Planes and Hypersonics Technologies

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A numerical study was performed to investigate the accuracy and validity of cold-gas simulation of actual hot scramjet exhaust within a Mach 10 free stream over a representative single-stageto-orbit airbreathing configuration. In particular, exhausts of various noncombusting chemistry models were studied to characterize their effects on the vehicle aftbody performance and the plume flow field definition. Two approximations of the hot scramjet combustion products were utilized to determine the requirement for expensive, multi-species numerical modeling, and to establish a baseline for the validation of cold-gas simulation. Cold-gas simulation at Mach 10 is shown to be a viable technique using an appropriate thermally perfect gas mixture for reproducing hot scramjet exhaust effects.

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Test description and preliminary pitot-pressure surveys for Langley Test Technique Demonstrator at Mach 6

Cited by 2 publications

References 3 publications

Enhanced control effector designs for airbreathing transatmospheric vehicles

Enhanced control effector designs for airbreathing transatmospheric vehicles

Exhaust gas modeling effects on hypersonic powered simulation at Mach 10

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