Investigation of pressure distributions and interference effects of blunt and sharp wing and body combinations at supersonic speeds
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Boatright, W. B.↗
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Results for “PRESSURE DISTRIBUTION - AIRFOILS”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Blade-section characteristics from pressure distributions on the sections of operating propellers
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Maynard, J. D.↗
Wing pressure distributions over the lift range of the convair xf-92a delta-wing airplane at subsonic and transonic speeds
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Jordan, G. H.↗
A method for predicting shock shapes and pressure distributions for a wide variety of blunt bodies at zero angle of attack
Relationship of shock standoff distance, at sonic and stagnation points, to body geometry of blunt bodies at zero angle of attack
Kaattari, G. E.↗
Axisymmetric static and dynamic buckling of spherical caps due to centrally distributed pressures.
Spherical caps axisymmetric static and dynamic buckling under load, using axisymmetric nonlinear elastic shell theory approximation and finite difference equations
Fulton, R. E.↗
Measured Heat-transfer and Pressure Distribution on the Apollo Face at a Mach Number of 8 and Estimates for Flight Conditions
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Jones, R. A.↗
Axisymmetric static and dynamic buckling of spherical caps due to centrally distributed pressures
Spherical caps axisymmetric static and dynamic buckling under load, using axisymmetric nonlinear elastic shell theory approximation and finite difference equations
Fulton, R. E.↗
Effects of boundary-layer displacement and leading-edge bluntness on pressure distribution, skin friction, and heat transfer of bodies at hypersonic speeds
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Bertram, M. H.↗
An Investigation of the Afterbody Pressure Distribution and Fin Loading Characteristics of a Specialized Store Configuration at Transonic Speeds
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Braden, J. A.↗
Flow fields, pressure distributions, and heat transfer for delta wings at hypersonic speeds
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Bertram, M. H.↗
Space shuttle: Preliminary pressure distributions on the 049 orbiter, orbiter in presence of H/O tank and orbiter in launch configuration
The 049 orbiter and launch configurations were tested in a trisonic wind tunnel to obtain preliminary loads information on the orbiter alone, orbiter in presence of the H/O tank and orbiter in the full launch configuration. The orbiter consisted of the baseline 049 double-delta wing, twin vertical stabilizers, seven degrees of dihedral and included abort rockets. The orbiter was mounted at minus 1.50 degree of incidence (fuselage centerline relative to H/O tank centerline) in the launch configuration. The solid rocket motors were mounted at a radial location of 21 degrees from the horizontal centerline of the H/O tank. The test was conducted over a Mach number range of 0.6 to 4.96. Nominal angle of attack and angle of sideslip ranges of minus 6 to plus 6 degrees were tested. In addition, the orbiter alone was tested over an angle of attack range of minus 6 to plus 26 degrees.
Hamilton, J. T.↗
Users manual for Streamtube Curvature Analysis: Analytical method for predicting the pressure distribution about a nacelle at transonic speeds, volume 1
The computer program, Streamtube Curvature Analysis, is described for the engineering user and for the programmer. The user oriented documentation includes a description of the mathematical governing equations, their use in the solution, and the method of solution. The general logical flow of the program is outlined and detailed instructions for program usage and operation are explained. General procedures for program use and the program capabilities and limitations are described. From the standpoint of the grammar, the overlay structure of the program is described. The various storage tables are defined and their uses explained. The input and output are discussed in detail. The program listing includes numerous comments so that the logical flow within the program is easily followed. A test case showing input data and output format is included as well as an error printout description.
Keith, J. S.↗
Users manual for Streamtube Curvature Analysis: Analytical method for predicting the pressure distribution about a nacelle at transonic speeds, volume 2
A special version of the Streamtube Curvature Analysis (STC) was been constructed to include a detached bow shock upstream of a plane or axisymmetric inlet. The bow wave is modeled using the method of Moeckel in conjunction with an approximate definition of the shock stand-off distance. A description of the Moeckel method and its implementation in the STC program are given.
Ferguson, D. R.↗
User manual for Streamtube Curvature Analysis: Analytical method for predicting the pressure distribution about a nacelle at transonic speeds, appendix
The computer program listing of Streamtube Curvature Analysis is presented. The listing includes explanatory statements and titles so that the program flow is readily discernable. The computer program listing is in CDC FORTRAN 2.3 source language form, except for three subroutines, GETIX, GETRLX, and SAVIX, which are in COMPOSE 1.1 language.
Keith, J. S.↗
Development of analytical methods of predicting the pressure distribution about a nacelle at transonic speeds: Exact solution
A computer program to predict the inviscid, transonic flow field about isolated nacelles was developed. The problem was to be formulated to solve Euler's equations without any approximation (such as small disturbances) and hence the terminology exact solution. The flow field was complicated by the presence of imbedded shock waves, an engine-inlet interface, and exhaust plumes. Furthermore, the transonic nacelles of interest had a very slender but blunt cowl lip. This created two distinct length scales, the length of the nacelle and the cowl lip radius that can differ by several orders of magnitude. These aspects of the flow field presented many numerical difficulties. The approach to the problem was to calculate the nacelle flow field using the method of time-dependent computations (TDC). Although at the time of the issuance of this contract, other approaches to transonic flow calculations existed, it was felt that TDC offered the most effective means of meeting the goals of the contract.
Grossman, B.↗