3 edition of A swept wing panel in a low speed flexible walled test section found in the catalog.
A swept wing panel in a low speed flexible walled test section
M. J. Goodyer
1988 by National Aeronautics and Space Administration, Scientific and Technical Information Division, For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va .
Written in English
|Statement||M. J. Goodyer.|
|Series||NASA contractor report -- 4106., NASA contractor report -- NASA CR-4106.|
|Contributions||United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.|
|The Physical Object|
Swept-wing cantilever monoplane. 35° sweepback at 25% of chord. Chord 28 ft ( m) at root, 9 ft 4 in ( m) at tip. Dihedral 7°. All-metal two-spar structure. Center-section continuous through fuselage. Two double-slotted flaps on each wing panel, separated by small trailing-edge spoiler surfaces, which provide lateral control in high. Serviceability: Features scroll compressor, variable-speed ECM motor, built-in domestic hot water heat exchanger, high- and low-pressure switches, moveable control panel, slide-in electric heat strips, TXV, and fully-insulated high-efficiency, cupronickel, coaxial water coil. All water connections are on the outside of cabinet for installation.
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The current interest in testing swept wing panels led to the work covered by this report, which describes the design of an adaptive-wall swept-wing test section for a low speed wind tunnel and gives test results for a wing panel swept at 40 deg. The test section has rigid flat sidewalls supporting the panel, and features flexible top and bottom Author: M.
Goodyer. Get this from a library. A swept wing panel in a low speed flexible walled test section. [M J Goodyer; United States. National Aeronautics and Space Administration. Joseph, katz & Allen, poltion, "Low Speed Aerodynamics From Wing Theory to panel Method".
Mc Graw-Hill, Study of the effects of wing sweep on the aerodynamic performance of a blended wing. CHARACTERISTICS AT LOW SPEED OF A SWEPT- WING AIRPLANE WITH SLOTTED FLAPS, AREA-SUCTION FLAPS, AND WING IEADING-EDGE DEVICES By Ralph L.
Maki and Harry A. James SUMMARY A low-speed wind-tunnel investigation of a high-wing airplane with an aspect ratio of and 36 sweepback of the quarter-chord line wasAuthor: Ralph L Maki, Harry A James. A swept wing panel in a low speed flexible walled test section. tunnel and gives test results for a wing panel swept at 40 deg.
The test section has rigid flat sidewalls supporting the panel. Cross section of 30° swept laminar suction wing with details of suction slots and suction chambers. laminar suction wing*9»10»11* of modified NACA section (in undis turbed flow direction) with the same chordwise pressure distribution at a = 0° as in the example of Section 3.
Wing chord and span were both seven feet. Book. Full-text available panel in a low speed flexible walled test section. for a low speed wind tunnel and gives test results for a wing panel swept at 40 deg.
The test section has rigid. A swept wing panel in a low speed flexible walled test section. for a low speed wind tunnel and gives test results for a wing panel swept at 40 deg.
The test section has rigid flat sidewalls. Consider a wing mounted in the test-section of a subsonic wind tunnel. The velocity of the airflow is ft/s. If the velocity at a point on the wing is ft/s, what is the pressure coefficient at this point. Therefore, new tests were conducted at the DNW-LST of the NLR in Emmeloord, a closed-loop atmospheric wind tunnel with a closed-wall test section.
Thanks to its low turbulence level (T u wing vibration was eliminated and the new measurement signals showed a high signal-to-noise ratio. Mary, in Engineering Turbulence Modelling and Experiments 5, Test case. A 70° sweep angle delta wing with sharp leading-edges has been chosen for the study, because the detailed experimental data of Mitchell et al.
(b) are available. The flow configuration is quite realistic: the Reynolds number, based on the root chord (c = m), and the upstream velocity (u ∞ = 24ms. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Wall streamlining eliminates, as far as experimentally possible, the top and bottom wall interference in low speed and transonic aerofoil testing.
A streamlining technique has been developed for low speeds which allows the testing of swept wing panels in low interference environments. Tuncer Cebeci, in Analysis of Turbulent Flows with Computer Programs (Third Edition), Data of Cumpsty and Head. In this experiment  the boundary-layer development was measured on the rear of a wing swept at °.
In addition to a sandwich configuration evaluated in Kirsch et al. () with the variation of the upper ply orientation, the present paper evaluate an anisotropic flexible wing test case derived from Patil wing and a two-ply composite laminates (carbon/epoxy TGC/M21) by sweeping both ply orientations (lower ply θ 1 and upper ply θ 2).
The low-speed separation constraint dramatically improves the high-lift capability of the wing at low-speed conditions. Additionally, the design changes required to satisfy the separation constraint have the effect of reducing passive load alleviation at the g maneuver loading, resulting in a substantial increase in structural weight.
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Featured. sults are given for a rectangular spar wing model. For theoretical studies a beam like structure is as-sumed. For the investigation of planned swept wing wind tunnel models with closed section ge-ometry, extended structural concepts are devel-oped.
2 Concepts for Flexible Wind Tunnel Wing Models Theoretical Investigation in Structural. Hydrodynamic Speed Control of Drives for Fluid Mechanic Installations A. Ernstberger Some Interesting Features of Two-Dimensional Wind Tunnel Testing at Low Supersonic Speeds in an Adaptive Flexible-Walled Test Section N.
Taylor and M. Goodyer A Half Wing Model Testing in 2-D Flexible Wall Adaptive Wind Tunnel. The fundamental low-speed physics of a separation-induced leading-edge vortex flow can be reviewed using a highly swept sharp-leading-edge delta wing, and examples are shown in Fig.
The upper-left image (Anderson (Reference Anderson 24)) illustrates the primary leading-edge vortex with primary separation at the sharp leading edge and. High subsonic flow over 3-D swept wing. DLR-F5 wing tested by Sobieczky is a m span wing with 20° sweep angle and an average chord length of mm.
The wing is mounted to the tunnel wall with a smooth blending region, and the angle of attack is set to be 2°. The square cross-section wind tunnel has dimensions of 1 × 1 × 4 meters. Increasing 10 kt trimmed at low speed has more effect on the stick force than increasing 10 kt trimmed at high speed.
the angle of attack of each blade, measured at the reference section: is optimum when the aircraft is in a stabilized cruising flight.
For a given Indicated airspeed (IAS), a swept wing compared to a straight wing of the. The wing configuration of a fixed-wing aircraft (including both gliders and powered aeroplanes) is its arrangement of lifting and related surfaces.
Aircraft designs are often classified by their wing configuration. For example, the Supermarine Spitfire is a conventional low wing cantilever monoplane of straight elliptical planform with moderate aspect ratio and slight dihedral.
(NACA RM L51F04) (Declassified from Confidential, 3/9/54) A qualitative investigation of the low-speed direc- tional behavior of a swept planing-tail hull was made in the Langley tank no. 2 in still water and still air with the use of a free self-propelled model. The configuration was directionally unstable over a range of low speed.
testing of a high speed, subsonic, low aspect ratio, for-ward swept wing with an advanced supercritical airfoil section for the purpose of determining its lift, drag, and pitching moment characteristics as compared to a similar aft swept wing. Tests were conducted at Mach numbers of.
Condition of the wing surface 4. Shape of the wing section and planiform 5. Speed of sound. Explain the stall progression on a swept wing. The lift distribution is such that low coeffeicient of lift at the tip and high coefficient at the root.
Since the stall will happen at. The load-bearing elements of the aircraft such as fuselage, longeron, stringer, bulkhead, covering, floor, horizontal stabilizer, vertical stabilizer, are fully partially made of prestressed structure comprising a pre-pressed member and a pre-tensioned member, and adding the filler to form units, the prestressed structure is obtained by producing a prestress greater than the maximum.
Pfenninger, W.; and Groth, E.: Low Drag Boundary Layer Suction Experiments in Flight on a Wing Glove of an FA Airplane with Suction through a Large Number of Fine Slots.
Boundary Layer and Flow Control, Volume 2, G. Lachman, ed., Pergamon Press,pp. – Google Scholar. Flight Characteristics of a Swept-Back Wing Jet Transport. Flight Tests of a 1/7 Scale North American X Airplane. Investigation of Low-Subsonic Flight Characteristic of Hypersonic Boost Glide.
Tests of Ground-Effect Machines Over Water. s: Low Speed Flight Characteristics of a Variable Sweep Fighter Model. A variable-sweep wing, colloquially known as a "swing wing", is an airplane wing, or set of wings, that may be swept back and then returned to its original straight position during allows the aircraft's shape to be modified in flight, and is therefore an example of a variable-geometry aircraft.
A straight wing is most efficient for low-speed flight, but for an aircraft designed for. As wind-speed requirements have increased, so too has the power needed to drive the giant fans. For example, the National Research Council of Canada operates a closed-circuit tunnel driven by a 9,hp motor to achieve ft/s velocity through the 30' x 30' x 75' test section.
Ames Air Force Base houses the largest low-speed wind tunnels. Joseph Katz and Allen Plotkin, Low-Speed Aerodynamics: From Wing Theory to Panel Methods, McGraw-Hill, Inc., Fourteen programs are in an appendix: Two-dimensional panel methods 1.
Grid Generator for van de Vooren airfoil shapes, includes velocity and pressure distributions Two-dimensional panel methods based on Neumann BC. subsequent flight test effort. TEST SETUP Model Description The model used in the present HLFC tests was a modified version of the one used in the LFC test of Ref [3,4].
It consisted of an 8-foot span section of a constant 20 ft chord 30° swept wing (see Fig 1). The front part of the model up to X/C = 20% on the wing upper surface. Maybe a little further forward. The steeper the angle of climb, the slower the launch. A positive climb angle is safer, wing tipwise.
I'd like to see at least a 15° climb angle for a 20lb, 5m swept wing. If we are thinking along the same lines, the bungee launch just gets the plane in the air, away from the ground at a good flying speed.
With the purpose of evaluating the adequacy of the NLR Panel Method with respect to the prediction of the flow around 3-D configurations with mechanical high-lift devices, potential flow calculations have been carried out for a swept-wing/body combination with part-span flaps at low speed.
The Grumman F9F/F-9 Cougar was a carrier-based fighter aircraft for the United States Navy and United States Marine on Grumman's earlier F9F Panther, the Cougar replaced the Panther's straight wing with a more modern swept was also increased.
The Navy considered the Cougar an updated version of the Panther, despite having a different official name, and thus Cougars. The Low Speed Tiltable Wind Tunnel SWT Rosen, J., Nyström, T: FLIGHT DYNAMICS OF LOW SPEED VEHICLES: Minimum Landing-Approach Distance for a VUK-T Sailplane: Stefanovic, Z., Cvetkovic, D: Preliminary Design of a Solar Powered Tailless Motorglider: Guglieri, G., Quagliotti, F: Center-of-Gravity and Lift Coefficient Limits of a Gliding.
Simon McBeath's book and the aero section in Milliken & Milliken are also worth the read. Test 14 blocked the lower half of the front, reducing drag to hp, Test 18 blocked the lower half of a MSA Type III airdam, reduced futher to hp.
The "V" shape wings you are talking about I think are what is called swept wing design for. And, a Jedelsky wing is as easy or easier to construct than a KFM wing (and yes, I have experience building both).
My first direct experience with a Jedelsky wing goes back to the mid 's, with a local design called a "Buffalo Chip", but the basic airfoil concept goes back far earlier than that.
The Aérospatiale/BAC Concorde (/ ˈ k ɒ ŋ k ɔːr d /) is a British–French turbojet-powered supersonic passenger airliner that was operated until It had a maximum speed over twice the speed of sound, at Mach (1, mph or 2, km/h at cruise altitude), with seating for 92 to passengers.
First flown inConcorde entered service in and operated for 27 years.The forward swept wing idea resulted from the transonic test of an aft swept wing of a Grumman configuration which had been proposed to satisfy the NASA HiMAT RFP (request for proposal).
The winning proposal was submitted by Rockwell, and the Rockwell HiMAT was built, flown, and is currently in the Smithsonian Air and Space Museum.The Messerschmitt Me Komet is a German interceptor aircraft designed for point-defence which is the only rocket-powered fighter aircraft ever to have been operational and the first piloted aircraft of any type to exceed km/h ( mph) in level flight.
Designed by Alexander Lippisch, its performance and aspects of its design were unprecedented.