Integrated Aeropropulsive Computational Fluid Dynamics Methodology for the Hyper-X Flight Experiment
| Autor: | Charles E. Cockrell, Tom N. Jentink, Arthur D. Dilley, Abdelkader Frendi, Walter C. Engelund, Robert D. Bittner |
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| Rok vydání: | 2001 |
| Předmět: | |
| Zdroj: | Journal of Spacecraft and Rockets. 38:836-843 |
| ISSN: | 1533-6794 0022-4650 |
| DOI: | 10.2514/2.3773 |
| Popis: | Computational e uid dynamics tools have been used extensively in the analysis and development of the X-43A Hyper-X Research Vehicle. A signiecant element of this analysis is the prediction of integrated vehicle aeropropulsive performance,which includes an integration of aerodynamic and propulsion eoweelds. Thedevelopment of the Mach7X-43Arequiredapree ightassessmentoflongitudinalandlateral-directionalaeropropulsivecharacteristics nearthetargeteight-testcondition.Thedevelopmentofthispree ightdatabasewasaccomplishedthroughextensive aerodynamic wind-tunnel testing and a combination of three-dimensional inviscid airframe calculations and cowlto-tail scramjet cycle analyses togenerate longitudinal performance increments between mission sequences. These increments were measured directly and validated through tests of the Hyper-X e ight engine and vehicle e owpath simulator in the NASA Langley Research Center 8-Foot High Temperature Tunnel. Predictions were reened with tip-to-tailNavier‐Stokescalculations,which alsoprovidedinformation onscramjetexhaustplumeexpansion inthe aftbody region. A qualitative assessment of lateral-directional stability characteristics was made through a series of tip-to-tail inviscid calculations, including a simulation of the powered scramjet eight-test condition. Additional comparisons with wind-tunnel forceand momentdataas well as surfacepressuremeasurements from theHyper-X e ight engine and vehicle eowpath simulator model and wind-tunnel testing were made to assess solution accuracy. |
| Databáze: | OpenAIRE |
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