02399oam 2200649I 450 991071389590332120200820090922.0(CKB)5470000002504730(OCoLC)1100474265(EXLCZ)99547000000250473020190508d1952 ua 0engurbn|||||||||txtrdacontentcrdamediacrrdacarrierThe aerodynamic design of high Mach number nozzles utilizing axisymmetric flow with application to a nozzle of square test section /by Ivan E. Beckwith, Herbert W. Ridyard, and Nancy CromerWashington, [D.C.] :National Advisory Committee for Aeronautics,1952.1 online resource (30 pages) illustrationsTechnical notes / National Advisory Committee for Aeronautics ;No. 2711"June 1952."No Federal Depository Library Program (FDLP) item number.Includes bibliographical references (page 18).NozzlesFluid dynamicsSupersonic nozzlesDesign and constructionAxial flowWind tunnel testingMathematical analysisAxial flowfastMathematical analysisfastNozzlesFluid dynamicsfastSupersonic nozzlesDesign and constructionfastWind tunnel testingfastNozzlesFluid dynamics.Supersonic nozzlesDesign and construction.Axial flow.Wind tunnel testing.Mathematical analysis.Axial flow.Mathematical analysis.NozzlesFluid dynamics.Supersonic nozzlesDesign and construction.Wind tunnel testing.Beckwith Ivan E.1403844Ridyard Herbert W.Cromer NancyUnited States.National Advisory Committee for Aeronautics,TRAALTRAALOCLCOCOPTRAALGPOBOOK9910713895903321The aerodynamic design of high Mach number nozzles utilizing axisymmetric flow with application to a nozzle of square test section3521478UNINA