| Aerodynamic Interference of Wing-Pylon Body Combinations at Low Subsonic Speeds. |
AUG 1973 |
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| Authors:
Kenneth Boland Walkley; Fred W. Martin; AUBURN UNIV AL DEPT OF AEROSPACE ENGINEERING
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 | A method for determining the subsonic aerodynamic interference between a planar wing with pylons and a single axisymmetric body has been developed and evaluated. The wing and body solutions were obtained independently using a simple horseshoe vortex system and a three-dimensional point source distribution, respectively. A vortex image system based on the two-dimensional theory of images was then added to the body to maintain the tangent-flow boundary condition in the ... |
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| Flutter Analysis and Recommended Testing of the F-4/C/D/E Aircraft Carrying Mk 84 or Mk 82 Bombs on the Outboard Wing Stations. |
SEP 1972 |
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| Authors:
C. E. Johnson; J. R. Smith; MCDONNELL AIRCRAFT CO ST LOUIS MO
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| Flutter analysis of the F-4C/D/E wing were conducted for two types of low-drag general purpose bombs mounted on the outboard wing pylons to investigate possible carriage to 650 knots equivalent airspeed or M - 1.4, whichever is less. The bombs analyzed were the MK84 suspended directly from the pylon and the MK82 installed on the multiple ejector rack (MER). Analytical wing flutter stability trends were investigated for a number of ... |
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| Investigation of the Flow Field Beneath the Wing of the F-4C Aircraft with Various External Stores at Mach Number 0.85. |
JUN 1972 |
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| Authors:
David W. Hill Jr; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
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| Tests were conducted to measure the velocity vector components in the flow field beneath the wing of the F-4C aircraft at Mach number 0.85. A conical-tip pressure probe was used to measure the velocity vectors beneath the wing with configuration combinations of pylons, Triple Ejection Rack (TER), Multiple Ejection Rack (MER), M-117, MK-81, and MK-84 stores. Results of the test indicate that the severity of the upwash and sidewash flow ... |
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| Prediction of Unsteady Aerodynamic Loadings on Non-Planar Wings and Wing-Tail Configurations in Supersonic Flow. Part I. Theoretical Development, Program Usage, and Application. |
MAR 1972 |
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| Authors:
Jack Morito II; Christopher J. Borland; John R. Hogley; BOEING CO RENTON WA COMMERCIAL AIRPLANE GROUP
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| A three-dimensional extension of the Mach Box technique was developed for the unsteady aerodynamic analysis of non-planar wings and wing-tail configurations in supersonic flow. Various refinement procedures were included to improve the accuracy of the results. A general purpose computer program was written for the CDC 6600. The program is capable of treating wing-tail combinations with or without vertical separation, longitudinal separation and dihedral on either surface. If a wing ... |
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| Effects of Moisture on Hawk Wings, |
29 AUG 1968 |
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| Authors:
Stewart B. Tulloch; ARMY MISSILE COMMAND REDSTONE ARSENAL AL SYSTEMS RESEARCH DIRECTORATE
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| Investigations were conducted to determine the effects of moisture on the integrity of HAWK fins or wings when the moisture is contained or retained in the inner areas of the wing. These effects appeared to be associated with the deterioration of adhesive strength by undermining the bond between the core and skin and the wicking of moisture into the glass fiber interface within the adhesive. (Author) |
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| SUPERSONIC WIND TUNNEL TESTS ON FOUR WINGS WITH SWEEPBACK, |
24 SEP 1945 |
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| Authors:
Allen E. Puckett; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
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| Tests of four airfoils with sweepback angles of 0, 30, 60, 67.5 deg. at a Mach number of 1.72 are compared with a simple theory. It is shown that little improvement in the lift-drag ratio is produced until the airfoil lies inside the Mach angle, but that the L/D ratio may be almost doubled using the proper sweepback angle. (Author) |
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(SWEPTBACK WINGS
