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Pitching moment

About: Pitching moment is a research topic. Over the lifetime, 3213 publications have been published within this topic receiving 38721 citations.


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Journal ArticleDOI
TL;DR: An improved delayed detached eddy simulation (IDDES) method based on the k-ω-SST turbulence model was applied to predict the unsteady vortex breakdown past an 80°/65° double-delta wing (DDW), where the angles of attack (AOAs) range from 30° to 40°.

24 citations

Journal ArticleDOI
TL;DR: A local flow measurement from an array of artificial hair sensors in a wind tunnel experiment is used with a feedforward artificial neural network to predict aerodynamic parameters such as lift coefficient, moment coefficient, free-stream velocity, and angle of attack on an airfoil.
Abstract: Distributed arrays of artificial hair sensors have bio-like sensing capabilities to obtain spatial and temporal surface flow information which is an important aspect of an effective fly-by-feel system. The spatiotemporal surface flow measurement enables further exploration of additional flow features such as flow stagnation, separation, and reattachment points. Due to their inherent robustness and fault tolerant capability, distributed arrays of hair sensors are well equipped to assess the aerodynamic and flow states in adverse conditions. In this paper, a local flow measurement from an array of artificial hair sensors in a wind tunnel experiment is used with a feedforward artificial neural network to predict aerodynamic parameters such as lift coefficient, moment coefficient, free-stream velocity, and angle of attack on an airfoil. We find the prediction error within 6% and 10% for lift and moment coefficients. The error for free-stream velocity and angle of attack were within 0.12 mph and 0.37 degrees. Knowledge of these parameters are key to finding the real time forces and moments which paves the way for effective control design to increase flight agility, stability, and maneuverability.

24 citations

Proceedings ArticleDOI
14 Jan 2002
TL;DR: In this article, a Smart Icing System for improved flight safety is proposed, in which microburst and gravity wave atmospheric disturbances are modeled, and their effects on the aircraft performance and control are compared to that of an icing encounter.
Abstract: Research is reported on aircraft performance and control in icing, related to the development of Smart Icing Systems for improved flight safety. Microburst and gravity wave atmospheric disturbances were modeled, and their effects on the aircraft performance and control were compared to that of an icing encounter. Simulations were run using a six degree- of-freedom computational flight dynamics model. The study showed that microbursts could easily be differentiated from icing encounters. On the other hand gravity waves are more difficult to differentiate. A plan was formulated for developing an envelope protection system effective in icing conditions. Two dimensional airfoil data were analyzed and showed promising results for prediction of envelope limit exceedence. Changes in unsteady hinge moments were especially effective in predicting stall. NOMENCLATURE Cd Airfoil drag coefficient Ch Airfoil hinge moment coefficient Ch,RMS Airfoil unsteady hinge moment coefficient Cl

24 citations

Proceedings ArticleDOI
09 Jul 2002
TL;DR: In this paper, a 30 percent scale wind tunnel model of a proposed uninhabited combat air vehicle under the DARPA/AFRL Smart Materials and Structures Development - Smart Wing Phase 2 program was constructed to demonstrate the applicability of smart control surfaces on advanced aircraft configurations.
Abstract: Northrop Grumman Corporation built and twice tested a 30 percent scale wind tunnel model of a proposed uninhabited combat air vehicle under the DARPA/AFRL Smart Materials and Structures Development - Smart Wing Phase 2 program to demonstrate the applicability of smart control surfaces on advanced aircraft configurations. The model constructed was a full span, sting mounted model with smart leading and trailing edge control surfaces on the right wing and conventional, hinged trailing edge control surfaces on the left wing. Among the performance benefits that were quantified were increased pitching moment, increased rolling moment and improved pressure distribution of the smart wing over the conventional wing. This paper present an overview of the result from the wind tunnel test performed at NASA Langley Research Center's Transonic Dynamic Tunnel in March 2000 and May 2001. Successful results included: (1) improved aileron effectiveness at high dynamic pressures, (2) demonstrated improvements in lateral and longitudinal effectiveness with smooth contoured smart trailing edge over conventional hinged control surfaces, (3) chordwise and spanwise shape control of the smart trailing edge control surface, and (4) smart trailing edge control surface deflection rates over 80 deg/sec.

24 citations

Journal ArticleDOI
TL;DR: In this article, the authors investigated six different geometric shapes of the airfoil to determine the best shape for the Fanwing with respect to the lift and drag coefficients and developed a computational fluid dynamics (CFD) code to find a more efficient configuration with lower power consumption and better performance.
Abstract: Purpose – Fanwing airfoil is a new lift‐generating section invented in 1997 by Patrick Peebles. The early shape of the airfoil has not changed until now. So far, no research has been done to change or modify the airfoil shape in order to improve its aerodynamic performance. In this paper, possibility of changing the airfoil shape to improve its aerodynamic performance is studied. For this purpose, six different geometric shapes of the airfoil are investigated numerically to determine the best airfoil on the basis of lift and drag coefficients. Flow over the airfoil is solved by developing a computational fluid dynamics (CFD) code. The purpose of this paper is to find a more efficient configuration for the Fanwing airfoil with lower power consumption and better performance.Design/methodology/approach – Flow over the airfoil is investigated by CFD. At the airfoil solid walls, the no slip condition is applied. Re‐Normalization Group k‐e model is used for turbulence modeling. The pressure‐velocity coupling is...

24 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202353
202294
202168
202076
201983
201886