[{"data":1,"prerenderedAt":-1},["ShallowReactive",2],{"detail-sidebar-cat-0-en-105":3,"doc-seo-182212-105":59,"doc-detail-182212-en":131},{"code":4,"msg":5,"data":6},0,"success",[7,13,18,23,28,33,38,43,48,51,55],{"id":8,"doc_module":4,"doc_module_name":9,"category_name":10,"show_sort_weight":11,"slug":12},1,"Document","Story & Novel",90,"story-novel",{"id":14,"doc_module":4,"doc_module_name":9,"category_name":15,"show_sort_weight":16,"slug":17},2,"Literature",80,"literature",{"id":19,"doc_module":4,"doc_module_name":9,"category_name":20,"show_sort_weight":21,"slug":22},4,"Exam",70,"exam",{"id":24,"doc_module":4,"doc_module_name":9,"category_name":25,"show_sort_weight":26,"slug":27},5,"Comic",60,"comic",{"id":29,"doc_module":4,"doc_module_name":9,"category_name":30,"show_sort_weight":31,"slug":32},6,"Technology",50,"technology",{"id":34,"doc_module":4,"doc_module_name":9,"category_name":35,"show_sort_weight":36,"slug":37},7,"Healthcare",40,"healthcare",{"id":39,"doc_module":4,"doc_module_name":9,"category_name":40,"show_sort_weight":41,"slug":42},8,"Research & Report",30,"research-report",{"id":44,"doc_module":4,"doc_module_name":9,"category_name":45,"show_sort_weight":46,"slug":47},9,"Religion & Spirituality",20,"religion-spirituality",{"id":46,"doc_module":4,"doc_module_name":9,"category_name":49,"show_sort_weight":46,"slug":50},"World Cup","world-cup",{"id":52,"doc_module":4,"doc_module_name":9,"category_name":53,"show_sort_weight":52,"slug":54},10,"Lifestyle","lifestyle",{"id":56,"doc_module":4,"doc_module_name":9,"category_name":57,"show_sort_weight":24,"slug":58},19,"General","general",{"code":4,"msg":60,"data":61},"ok",{"site_id":62,"language":63,"slug":64,"title":65,"keywords":66,"description":67,"schema_data":68,"social_meta":124,"head_meta":126,"extra_data":128,"updated_unix":130},105,"en","axial-flow-compressor-computer-program-for-calculating-off-design-performance-program-iv-summary","Axial Flow Compressor - Computer Program for Calculating Off-Design Performance (Program IV) - Summary","","Technical objectives of the NASA contract included generating an IBM 7094 computer program for calculating off-design aerodynamic performance of multistage axial-flow compressors. The method accounts for variable specific heat and full radial equilibrium of the flow, incorporating streamline curvature and radial gradients in total enthalpy and entropy. The computation is iterative, using a total pressure loss coefficient formed from a correlated reference loss plus an off-reference increment. The program supports up to 12 stages, accepts detailed geometry and inlet conditions, and outputs performance results including loss and incidence/deviation 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is the purpose of the computer program described in the report?","Question",{"text":113,"@type":114},"It calculates off-design aerodynamic performance for multistage axial-flow compressors, accounting for variable specific heat and full radial equilibrium of the flow.","Answer",{"name":116,"@type":111,"acceptedAnswer":117},"How does the program determine efficiencies in the performance calculation?",{"text":118,"@type":114},"Efficiencies are determined iteratively using a total pressure loss coefficient composed of a correlated reference loss coefficient plus an off-reference increment.",{"name":120,"@type":111,"acceptedAnswer":121},"What compressor geometries and inputs does the program support?",{"text":122,"@type":114},"It considers specified compressor geometry with up to 12 stages and accepts hub/tip blockages and geometry at each axial station, along with uniform inlet total temperature and 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CompressorComputer Program for CalculatingOff-Design Performance(Program IV)\n\nby  \nH.F.Creveling and R.H.Carmody  \n## Prepared forNATIONAL AERONAUTICS AND SPACE ADMINISTRATION\n\nContract NAS3-7277  \nTechnical ManagementNASA-Lewis Research CenterCleveland,Ohio  \nLewis Proiect Manager:William L.Beede  \nLewis Reseach Advisor:L.Joseph Herrig  \nAllison Division·General MotorsIndianapolis,Indiana  \n▲  \nNOTICE  \nThis report was prepared as an account of Government sponsoredwork.Neither the United States,nor the National Aeronautics andSpace Administration(NASA),nor any person acting on behalf ofNASA:  \nA.Makes any warranty or representation,expressed or im-plied,with respect to the accuracy,completeness,orusefulness of the information contained in this report,orthat the use of any information,apparatus,method,orprocess disclosed in this report may not infringe privatelyowned rights;or  \nB.Assumes any liabilities with respect to the use of,or fordamages resulting from the use of any information,appara-tus,method or process disclosed in this report.  \nAs used above,\"person acting on behalf of NASA\"includes any em-ployee or contractor of NASA,or employee of such contractor,tothe extent that such employee or contractor of NASA,or employeeof such contractor prepares,disseminates,or provides access to,any information pursuant to his employment or contract with NASA,or his employment with such contractor.  \nRequests for copies of this report should be referred to  \nNational Aeronautics and Space AdministrationScientific and Technical Information FacilityP.O,Box 33College Park,Maryland 20740  \nNOTICE  \nTHIS DOCUMENT HAS BEEN REPRODUCEDFROM THE BEST COPY FURNISHED US BYTHE SPONSORING AGENCY.ALTHOUGH ITIS RECOGNIZED THAT CERTAIN PORTIONSARE ILLEGIBLE,IT IS BEING RELEASEDIN THE INTEREST OF MAKING AVAILABLEAS MUCH INFORMATION AS POSSIBLE.  \nI  \nTABLE OF CONTENTS  \nTitle  \nPage  \nSummary………………………………………………………………………………………………………………………………1  \nIntroduction…………………………………………………………………………………………………………………………………………………2  \nSymbols…………………………………………………………………………………………………………………………………………………………3  \nTechnical Discussion…………………………………………………………………………………………………………………………9  \nDevelopment of Program Logic ……………………………………………………………………………………………14  \nReferences………………………………………………………………………………………………………………………………………………16  \nAppendix A—Systems of Equations and Computations…………………………………………A-1  \nAppendix B一Fortran IV Source Deck Listing………………………………B-1  \nAppendix C一Program Flow Charts……………………………………………C-1  \nAppendix D—Input Format and Sample Data Set………………………………………………………D-1  \nAppendix E—Output Format—Sample Performance Problem……………………E-1  \n## COMPUTER PROGRAM FOR CALCULATING OFF-DESIGN PERFORMANCE\n\nOF MULTISTAGE AXIAL-FLOW COMPRESSORS  \nby  \nH.F.Creveling and R.H.Carmody  \n## SUMMARY\n\nThe technical objectives of the contract included generating a computer(IBM 7094)programmed axial-flow compressor off-design aerodynamic per-formance calculation which accounts for variable specific heat and full radialequilibrium of the flow,including streamline curvature and radial gradientsin total enthalpy and entropy.The resulting performance computation is iter-ative,with efficiencies determined from a total pressure loss coefficient whichis taken as the sum of a calculated reference loss coefficient and an off-refer-ence increment in loss coefficient.The reference loss is established throughthe use of correlated blade element profile loss data and the loss associated witha normal shock in the blade passage,where appropriate,for diffusion factorsfrom 0 to 1.0 and Mach numbers from 0 to 1.6.A compressor of specifiedgeometry is considered and energy addition for a given flow rate and rotationalspeed is determined through the use of blade element performance data con-cerning reference incidence angle and deviation angle.  \nTabular data for loss,incidence angle,and deviation angle are availablein the program for NACA 65-series an","cbCaioyJ6arNCEUq","https://ap.wps.com/l/cbCaioyJ6arNCEUq","pdf",7653832,258,"English","# Summary\n# Introduction\n## Program description and objectives\n## Iterative performance calculation approach","[{\"question\":\"What is the purpose of the computer program described in the report?\",\"answer\":\"It calculates off-design aerodynamic performance for multistage axial-flow compressors, accounting for variable specific heat and full radial equilibrium of the flow.\"},{\"question\":\"How does the program determine efficiencies in the performance calculation?\",\"answer\":\"Efficiencies are determined iteratively using a total pressure loss coefficient composed of a correlated reference loss coefficient plus an off-reference increment.\"},{\"question\":\"What compressor geometries and inputs does the program support?\",\"answer\":\"It considers specified compressor geometry with up to 12 stages and accepts hub/tip blockages and geometry at each axial station, along with uniform inlet total temperature and pressure.\"}]","Axial Flow Compressor - Computer Program for Calculating Off-Design Performance (Program IV) - Summary | PDF",650]