31 research outputs found
Experimental Investigation of Drag of Afterbodies with Exiting Jet at High Subsonic Mach Numbers
Get PDFEffects of leading-edge devices and trailing-edge flaps on longitudinal characteristics of two 47.7 degree sweptback wings of aspect ratios 5.1 and 6.0 at a Reynolds number of 6.0 x 10(exp 6)
Get PDFPreliminary Investigation of Methods to Increase Base Pressure of Plug Nozzles at Mach 0.9
Get PDFThe effects of various afterbody changes on the base pressure of a nacelle-type isentropic plug nozzle installation operating at lower-than-design jet pressure ratios were investigated at a Mach number of 0.9. Although the estimates of the net propulsive force contain some uncertainties, the results indicate that both a plain-ring base shroud and a circular-arc boattail fairing reduced the loss in net propulsive force experienced with a cylindrical nacelle installation of the plug nozzle
Low-speed Longitudinal Aerodynamic Characteristics of a Twisted and Cambered Wing of 45 Degree Sweepback and Aspect Ratio 8 with and Without High-lift and Stall-control Devices and a Fuselage at Reynolds Numbers from 1.5 x 10(exp 6) to 4.8 x 10(exp 6
Get PDFA Three-Dimensional Flow Expander as a Device to Increase the Mach Number in a Supersonic Wind Tunnel
Get PDFA preliminary investigation of a simple 5 deg conical-flow expander was made to determine the feasibility of using this type of device to increase the Mach number in the test section of a supersonic wind tunnel. The inlet-to-exit area ratio of the nozzle was that required to increase one-dimensional flow from a Mach number of 3.88 to 5.5. The Mach numbers obtained at the expander exit varied from about 5.1 at the centerline to about 5.4 near the walls. No difficulty in operation of the main wind tunnel was experienced
Yaw Characteristics of a 52 Degree Sweptback Wing of NACA 64(sub 1)-112 Section with a Fuselage and with Leading-edge and Split Flaps at Reynolds Numbers from 1.93 x 10(exp 6) to 6.00 x 10(exp 6)
Get PDFPressure-distribution Measurements over an Extensible Leading-edge Flap on Two Wings Having Leading-edge Sweep of 42 Degrees and 52 Degrees
Get PDFLongitudinal Characteristics of Two 47.7 Degree Sweptback Wings with Aspect Ratios of 5.1 and 6.0 at Reynolds Numbers up to 10 x 10(exp 6)
Get PDFInterference effects at Mach 1.9 on a horizontal tail due to trailing shock waves from an axisymmetric body with an exiting jet
Get PDFInvestigation of low-speed lateral control and hinge-moment characteristics of a 20-percent-chord plain aileron on a 47.7 degrees sweptback wing of aspect ratio 5.1 at a Reynolds number of 6.0 x 10(exp 6)
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