Transonic Drag Prediction Using an Unstructured Multigrid Solver


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NASA/CR-2002-211455 ICASE Report No. 2002-5 Transonic Drag Prediction Using an Unstructured Multigrid Solver Dimitri J. Mavriplis ICASE, Hampton, Virginia David W. Levy Cessna Aircraft Company, Wichita, Kansas April 2002 Report Documentation Page Report Date 00APR2002 Report Type N/A Dates Covered (from... to) Contract Number Grant Number Program Element Number Author(s) Dimitri J. Mavriplis, David W. Levy Project Number Task Number Work Unit Number Performing Organization Name(s) and Addres
  NASA/CR-2002-211455ICASE Report No. 2002-5 Transonic Drag Prediction Using an UnstructuredMultigrid Solver  Dimitri J. Mavriplis ICASE, Hampton, Virginia David W. LevyCessna Aircraft Company, Wichita, Kansas April 2002  Report Documentation Page Report Date  00APR2002 Report Type  N/A Dates Covered (from... to)  - Title and Subtitle  Transonic Drag Prediction Using an UnstructuredMultigrid Solver Contract Number   Grant Number   Program Element Number   Author(s)  Dimitri J. Mavriplis, David W. Levy Project Number   Task Number   Work Unit Number   Performing Organization Name(s) and Address(es)  ICASE Mail Stop 132C NASA Langley Research CenterHampton, VA 23681-2199 Performing Organization Report Number   Sponsoring/Monitoring Agency Name(s) andAddress(es)   Sponsor/Monitor’s Acronym(s)   Sponsor/Monitor’s Report Number(s)   Distribution/Availability Statement  Approved for public release, distribution unlimited Supplementary Notes  ICASE Report No. 2002-5 Abstract  This paper summarizes the results obtained with the NSU3D unstructured multigrid solver for the AIAADrag Prediction Workshop held in Anaheim, CA, June 2001. The test case for the workshop consists of awing-body con guration at transonic ow conditions. Flow analyses for a complete test matrix of liftcoecient values and Mach numbers at a constant Reynolds number are performed, thus producing a set of drag polars and drag rise curves which are compared with experimental data. Results were obtainedindependently by both authors using an identical baseline grid, and dierent re ned grids. Most cases wererun in parallel on commodity cluster-type machines while the largest cases were run on an SGI Originmachine using 128 processors. The objective of this paper is to study the accuracy of the subjectunstructured grid solver for predicting drag in the transonic cruise regime, to assess the eciency of themethod in terms of convergence, cpu time and memory, and to determine the eects of grid resolution onthis predictive ability and its computational eciency. A good predictive ability is demonstrated over a widerange of conditions, although accuracy was found to degrade for cases at higher Mach numbers and liftvalues where increasing amounts of ow separation occur. The ability to rapidly compute large numbers of cases at varying ow conditions using an unstructured solver on inexpensive clusters of commoditycomputers is also demonstrated. 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