02775nam a2200349Ia 4500012182974MiAaHDL20121218000000.0m d cr bn ---auaua060814s1944 vau t f000 0 eng dsdr-ufdc020953679sdr-ufdc.990209536790306597(OCoLC)70891407FUGFUGY 3.N 21/5:11/L-216NACA L-216Kaplan, Carl.The flow of a compressible fluid past a circular arc profile /Carl Kaplan.NACA wartime reportsLangley Field, VA :Langley Memorial Aeronautical Laboratory,1944.69, [20] p. ;28 cm."NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution."FU"Report date October 1944."FU"Originally issued October 1944 as Advance Restricted Report L4G15."FU"Report no. L-216."FUSummary: The Ackeret iteration process is utilized to obtain higher approximations than that of Prandtl and Glauert for the flow of a compressible fluid past a circular arc profile. The procedure is to expand the velocity potential in a power series of the camber coefficient. The first two terms of the development correspond to the Prandtl-Glauert approximation and yield the well-known correction to the circulation about the profile. The second approximation, involving the square of the camber coefficient, improves the velocity and pressure fields but yields no new results with regard tot he circulation, since the circulation about the profile is an odd function of the camber coefficient. The third approximation, involving the cube of the camber coefficient, permits the use of higher values of the camber coefficient and furthermore yields an improvement to the Prandtl-Glauert rule with regard to the effect of compressibility on the circulation of the circular arc profile. Numerical examples with tables and graphs illustrate the results of the analysis.Also available in electronic format.FUMode of access: Internet.Aerodynamics.Compressibility.Mach number.United States.National Advisory Committee for Aeronautics.Langley Aeronautical Laboratory.NACA collection.01218297420120130145242.020121218000000.020171120114410.02017-11-20T19:57:15Z2014-05-22T20:00:04ZSDR-UFDCEX LIBRIS - ALEPHprepare.pl-004-007BKsdr-ufdc020953679ufl1SDRIUFLufl1.ark:/13960/t76t1n75nFU020953679ia.flowofcompressib00langia.flowofcompressib00langFUIUFL20171120iaufl1.ark:/13960/t76t1n75n1944pdbibUS fed docFUUFDC20251113googleufl.312620810328891944pdbibUS fed doc