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Tuesday, August 4, 2020 | History

3 edition of Low speed analysis of mission adaptive flaps on a high speed civil transport configuration found in the catalog.

Low speed analysis of mission adaptive flaps on a high speed civil transport configuration

Victor R. Lessard

Low speed analysis of mission adaptive flaps on a high speed civil transport configuration

by Victor R. Lessard

  • 113 Want to read
  • 21 Currently reading

Published by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributor in Hampton, Va, Springfield, VA .
Written in English

    Subjects:
  • Thin films.,
  • Low speed.,
  • Flapping.,
  • Turbulence models.,
  • Pitching moments.,
  • Mathematical models.,
  • Leading edge flaps.,
  • Boundary layer separation.,
  • Baldwin-Lomax turbulence model.

  • Edition Notes

    StatementVictor R. Lessard.
    Series[NASA contractor report] -- NASA/CR-1999-209524., NASA contractor report -- NASA CR-1999-209524.
    ContributionsLangley Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15567867M

    Civil Rotorcraft Market Current Outlook 4" Civil Market is projected to continue growth over next decade1 $B in ⇒ $B in Improvement in global deliveries from % during Near-term – Projections show civil sector sales increasing while military sales are decreasing; value of production about equal in civil vs military sales by Specific issues addressed include high-speed civil-transport air-breathing propulsion, generic hypersonic inlet-module analysis, an investigation on spoiler effects, high-alpha vehicle dynamics, space-station resource node flow-field analysis, a numerical simulation of sabot discard aerodynamics, and vortex control using pneumatic blowing.

    Finally, the measurements of the angle of attack and the elevator angle were taken at different speed sets for both flaps on and flaps off. By measuring time and the air speed in the tunnel using a sensitive manometer connected to static pressure taps on the tunnel contraction, aerodynamic derivatives are determined for respective analysis and. PROBLEM TO BE SOLVED: To provide an FLADE (fan on blade) aircraft gas turbine engine having a fixed geometry inlet duct 4. SOLUTION: This gas turbine engine comprises an engine inlet 13 including a fan inlet 11 to a fan section and an annular FLADE inlet 8 to the FLADE duct 3. A fixed geometry inlet duct 4 is in direct flow communication with the engine inlet

    Low-speed aerodynamic characteristics of a transport model having ̊swept low wing with supercritical airfoil, double-slotted flaps, and T-tail or low tail / (Washington, D.C.: National Aeronautics and Space Administration ; [Springfield, Va. VARIABLE-CAMBER SYSTEMS INTEGRATION AND OPERATIONAL PERFORMANCE OF THE AFTI/F MISSION ADAPTIVE WING Authors: John W capabilities for the design and analysis of high-speed civil transport control systems, and to identify the shortcomings and issues. system disciplines to develop a high-speed civil transport. The mission and.


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Low speed analysis of mission adaptive flaps on a high speed civil transport configuration by Victor R. Lessard Download PDF EPUB FB2

Low Speed Analysis of Mission Adaptive Flaps on a High Speed Civil Transport Configuration Summary Thin-layer Navier-Stokes analyses were done on a high speed civil transport configuration with mission adaptive leading-edge flaps.

The flow conditions simulated were Mach and. Get this from a library. Low speed analysis of mission adaptive flaps on a high speed civil transport configuration. [Victor R Lessard; Langley Research Center.].

Thin-layer Navier-Stokes analyses were done on a high speed civil transport configuration with mission adaptive leading-edge flaps. The flow conditions simulated were Mach = and Reynolds number of million for angles-of-attack ranging from 0 to 18 degrees.

Two turbulence closure models were : Victor R. Lessard. Thin-layer Navier-Stokes analyses were done on a high speed civil transport configuration with mission adaptive leading-edge flaps.

The flow conditions simulated were Mach =. Full text of "Low-Speed Investigation of Upper-Surface Leading-Edge Blowing on a High-Speed Civil Transport Configuration" See other formats NASA/TP Low-Speed Investigation of Upper-Surface Leading-Edge Blowing on a High-Speed Civil Transport Configuration Daniel W.

Banks, Brenda E. Gile Laflin, Guy T. Kemmerly, and Bryan A. Abstract and 16 A Study was conducted to configure and analyze a passenger, Mach 4 high-speed civil transport with a design range of n.

The design mission assumed an all-supersonic cruise segment and no community noise or sonic boom constraints. This is true for both large and small planes. Even for a Cessna S, 10 degrees of flaps are recommended for takeoff.

Once the plane is off the ground, the flaps are retracted, the camber is reduced, and the aircraft accelerates to cruise speed. Landing Flap Settings. When you're landing, you typically extend your flaps to their maximum setting.

These were used to predict % reductions in takeoff and landing distances for a three-dimensional advanced subsonic transport configuration employing a simplified pneumatic high. 1. Introduction. Rapid increasing demands of civil aviation are driven by the high-speed transport requirements of growing middle class, global economic growth and urbanization.

1 With growing urbanization, there is a greater demand to connect the world’s cities. Sinceair transportation has grown at a fast around 5% Compound Annual Growth Rate (CAGR), and.

The McDonnell Douglas F Eagle is an American twin-engine, all-weather tactical fighter aircraft designed by McDonnell Douglas (now part of Boeing).Following reviews of proposals, the United States Air Force selected McDonnell Douglas's design in to meet the service's need for a dedicated air superiority Eagle first flew in Julyand entered service in An attached flow flap, shown on the model in figure 5, was also designed for the entire wing leading-edge.

The flap was designed using Carlson's wing design code (reference 10) and is referred to as a mission adaptive flap because the local flap deflection angle increases as a func-tion of wing span to account for the increasing upwash field. GD speed (fig.1) is the engine-out operating speed in clean configuration.

It provides an estimate of the speed for best lift-to-drag ratio. GD speed is the managed speed target in CONF CLEAN when the FMS approach phase is activated.

It is also the recommended speed to extend flaps to CONF 1 and for a holding in clean configuration. First, a preliminary performance assessment at low speed has been done in a two-dimensional flow for a pre-designed landing configuration considering a standard flap.

Figure 14 presents the computed C L (α) curves for a geometry considering a droop nose or not. As for any leading edge devices, the use of a droop nose leads to an increase of. Federal Aviation Administration. adaptive Prior art date Legal status (The legal status is an assumption and is not a legal conclusion.

Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.) Granted Application number US12/, Other versions USB2 (en Inventor Roelof Vos Ronald M. Barrett.

Improved low-speed, high-lift aerodynamic performance for highly swept wings typical of a configuration designed for supersonic flight can positively impact noise. Although the propulsion system is the major contributor to noise during takeoff, as noted earlier the vehicle flight path and operations also affect noise impact on the community.

The upper-surface vortex flap, Fig. 52, Insert a, has some unique aerodynamic characteristics: at low angles of attack, a vortex forms inboard of the flap whose suction generates drag on the flap but also increases lift on the exposed wing area; at high angles of attack, a dominant vortex develops in front of the flap while the inboard vortex.

Use of Morphing Technology at Low-Speed. All the previously mentioned benefits provided by the use of morphing technology on an aircraft are for high speed flight conditions. However, the use of morphing technology at low speed conditions, namely take-off or landing, can also be the source of significant performance improvements.

Managed Speed will remain a constant VAPP ( Kts) unless S High Speed Protection Indicates the speed (VMO + 4 kt or MMO + ) at which an overspeed warning will occur and High Speed Protection becomes active. The actual configuration is used for the overspeed warning. Accident Analysis and Prevention (): 42(6), Rosén, Erik.

“Pedestrian Fatality Risk.” Presented in Abo, Rosén, Erik, and Ulrich Sander. "Pedestrian Fatality Risk as a Function of Car Impact Speed." Accident Analysis and Prevention (): 41(3), “Vehicle Stopping Distance and Time.” University of.

TACTICAL FLIGHT MISSION PLANNING AND MAP PREPARATION GUIDE. References. TC (October ), FM (May ) FM 4 .GS ground speed, knots GW gross weight, lb g, G acceleration due to gravity, ft/sec2 HQ handling qualities HSCT High-Speed Civil Transport HSR high-speed research HUD head-up display altitude of center of gravity, ft aircraft moment of inertia about body X-axis, slug-ft2 product of inertia about X and Z body axes, slug-ft2.with a High-Speed Civil Transport (HSCT) configura-tion, designated as the Technology Concept Airplane (TCA) within NASA’s High-Speed Research (HSR) program at low-speed, high-lift conditions.

Such com-plex separated flows, emanating either from surface discontinuities (e.g., wing sharp leading edges and.