Topic
Lift-induced drag
About: Lift-induced drag is a research topic. Over the lifetime, 2861 publications have been published within this topic receiving 41094 citations.
Papers published on a yearly basis
Papers
More filters
TL;DR: In this article, the authors proposed an effective numerical model based on the computational fluid dynamics (CFD) approach to obtain the flow structure around a passenger car with a rear spoiler.
Abstract: Now a days demand of a high speed car is increasing in which vehicle stability is of major concern. Forces like drag& lift, weight, side forces and thrust acts on a vehicle when moving on road which significantly affect the fuel consumption The drag force is produced by relative motion between air and vehicle and about 60% of total drag is produced at the rear end. Reduction of drag force at the rear end improves the fuel utilization. This work aims to reduce the drag force which improves fuel utilization and protects environment as well. In the stage of work a sedan car with different types of spoilers are used to reduce the aerodynamic drag force. The design of sedan car has been done on CATIA-2010 and the same is used for analysis in ANSYS-(fluent). The analysis is done for finding out drag and lift forces at different velocities, and spoilers. This study proposes an effective numerical model based on the computational fluid dynamics (CFD) approach to obtain the flow structure around a passenger car with a rear spoiler.
12 citations
09 Jan 2012
TL;DR: In this article, the influence of plasma actuation on flow control over an oscillating NACA 0012 airfoil is theoretically predicted and the results show that depending upon the location of the actuator up to 29.2% more lift and 12.5% less drag can be obtained.
Abstract: The two dimensional flow past an oscillating NACA 0012 airfoil at Re = 1.35 x 10 is simulated using a large eddy simulation model and subsequently, the influence of plasma actuation on flow control over such an oscillating airfoil is theoretically predicted. Simulation results without plasma actuation were benchmarked with earlier reported experimental data. The formation, growth and separation of the vortical structures along the airfoil have been studied without and with the influence of plasma body force generated by the dielectric barrier discharge actuators. We present results for plasma actuators placed at the leading edge, mid chord and trailing edge locations in both co-flow and counter flow configurations. The force due to the actuator for a length of 1.5-2.0 cm varied in the range of 4-15 kN/m and this was predicted from a force approximation model. Our results show that depending upon the location of the actuator up to 29.2% more lift and 12.5% less drag can be obtained. Such predicted improvement in the lift and drag characteristics through the use of plasma actuation indicate a very useful application of such flow control device in enhancing the performance of oscillating airfoils.
12 citations
13 Sep 2010
TL;DR: In this article, the authors describe a method to produce an approximate loft worthy of analysis using higher order methods, and draw some observations concerning the wing plan-form selection process, which can be used to evaluate the performance of a wing.
Abstract: The aircraft conceptual design process traditionally determines the size, shape, specification and configuration of an airframe to meet specific performance requirements. A successful design process must incorporate synthetic (generative) as well as analytic elements. In the conceptual design process the overall planform and span-wise thickness distribution of a wing must be defined. However, if the performance of the concept wing is to be properly verified, the wing geometry must exhibit approximately correct drag divergence behavior at an expected induced drag level. This paper describes a method to produce an approximate loft worthy of analysis using higher order methods, and draws some observations concerning the wing planform selection process.
11 citations
01 Jul 1969
11 citations
TL;DR: In this article, a flight-test method is described from which propulsive efficiency as well as parasite and induced drag coefficients can be directly determined using relatively simple instrumentation and analysis techniques.
Abstract: A flight-test method is described from which propulsive efficiency as well as parasite and induced drag coefficients can be directly determined using relatively simple instrumentation and analysis techniques. The method uses information contained in the transient response in airspeed for a small power change in level flight in addition to the usual measurement of power required for level flight. Measurements of pitch angle and longitudinal and normal acceleration are eliminated. The theoretical basis for the method, the analytical techniques used, and the results of application of the method to flight-test data are presented. Flight-test data showed performance parameters measured with a standard deviation of about 0.8% for propulsive efficiency, 0.3% for parasite drag coefficient, and 8% for the airplane efficiency factor, e.
11 citations