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Chaitanya Kumar Konda

Publications and source records attributed to Chaitanya Kumar Konda.

2 recordsLinked to original sources

FGM optimization in complex domains using Gaussian process regression based profile generation algorithm

This manuscript addresses the challenge of designing functionally graded materials (FGMs) for arbitrary-shaped domains. Towards this goal, the present work proposes a generic volume fraction profile generation algorithm based on Gaussian Process Regression (GPR). The proposed algorithm can handle complex-shaped domains and generate smooth FGM profiles while adhering to the specified volume fraction values at boundaries/part of boundaries. The resulting design space from GPR comprises diverse profiles, enhancing the potential for discovering optimal configurations. Further, the algorithm allows the user to control the smoothness of the underlying profiles and the size of the design space through a length scale parameter. Further, the proposed profile generation scheme is coupled with the genetic algorithm to find the optimum FGM profiles for a given application. To make the genetic algorithm consistent with the GPR profile generation scheme, the standard simulated binary crossover operator in the genetic algorithm has been modified with a projection operator. We present numerous thermoelastic optimization examples to demonstrate the efficacy of the proposed profile generation algorithm and optimization framework.

cs.LG↗

Aerodynamic Study of Leading-Edge Protuberance to Improve the Performance of NACA 0009 Blade

Symmetric NACA airfoils tend to undergo abrupt stall characteristics at higher angle of attacks. The abrupt stall has deteriorating effect on lift as well as the efficiency of the airfoils. Abruptness in stall restricts the airfoil to operate only at lower angle of attacks. So, in order to improve the efficiency of airfoils at higher angle of attacks and make it suitable for operation over higher range of angle of attacks, there are many flow control techniques. One such technique is addition of leading-edge protuberance. Leading-edge protuberances are the leading-edge modification of the wing. Leading-edge of the wing is modified with sinusoidal structural modification. This modification has two parameters i.e., Pitch and Amplitude. Many configurations of the protuberances can be obtained by changing the Pitch to Amplitude ratio of the protuberance. In the present work, the Reynolds number is 50k for NACA 0009. The Pitch to Amplitude ratio is varied from PAR1 to PAR27. PAR6 is found to be the better case which has higher lift and efficiency in the post-stall angle of attacks. At the deep stalling AOA of the baseline, i.e., at 13.6o, PAR6 is found to have the highest increase in lift and efficiency compared to the other post stalling AOAs with it having around 39.6% more lift and 27.3% more efficiency compared to the baseline.

cs.CE↗