The logic of the program can conveniently be described by the follow.
boundary-layer displacement thickness, a nonuni-įarm but unidirectional onset flow field, and the presence of air intakes. , and readjusts this initial solution toĪccount for the effects of -the. Th© first, program - FLOWBOBY - performs a potential flow solution by the Sample inputs and outputs are also given to provide refer-Įnces for proper program executions at other computing installatio ns. to present these programs with their complete The procedures have been described Īnd coded into two FORTRAN computer programs. Purpose of reducing the cruise, drag of light aircraft for better performanceĪnd fuel economy through studying the effects arising from modifications. 133įor_the past contract year a research program has been conducted for the Example of stereo frames of stereoscopic view. Orientation of body with respect to_body reference axes _ġ0. Example of orthographic projection - 129ħ. Illustration of points used in averaging and interpolatingĦ. Definition, of, angles for specification of vortex ring(s),ĥ. Rings as well as the induced velocity of such anģ. Typical plot of the location and radii of the vortex Orientation of body with respect to the body referenceĢ. Sufficient air flow for cooling the engine.ĮLOWBODY PROGRAM - USER* S INSTRUCTIONS. Tionsjor flow port locations to_reduce the cruise drag as well as to provide The programs may : be effectively used to determine the appropriate body modificatt. arisingįrom the engine cowl shape and the forward fnselage_area and also that resultingįrom the cooling air mass flowing through intake. The report represents in part an effort to reduce the cruise drag of light -Īircraft_.throvgh an analytical study of the contributions to the drag. Shape of a body to satisfy particular needs without a significant amount. The boundary-layer displacement thickness, a nonuniform but unidirectional onsetįlow field, and the presence of air intakes and exhausts.The second program isĮffectually a geometry pa cka ge which. Panel method and readjusts this initial solution to account for the effects o!. The first program performs a potential flow solution by a well-known Solution of the viscous f Iowl over an.arbitrary non-lifting three-dimensionalīody. Of two computer programs which are especially useful in obtaining an approximate This reportĬonsists of the listings, user's instructions, sample inputs, and sample outputs accurate estimation of its lift and drag. The successful prediction of the performance Otf„a new or modified aircraftĭepends heavily on an. (North Carolina State Univ.) 203 p Unclas. SHAPES AND FLOW POti ' 7 OC AT IONS FOB MINIMUMĭBAG WITH EFFECTIVE EdfilME COOLING.
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Full text of " NASA Technical Reports Server (NTRS) 19830008018: A study of optimum cowl shapes and flow port locations for minimum drag with effective engine cooling, volume 2"
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