RANCANG BANGUN ALAT UKUR GAYA LIFT DRAG DAN
MOMEN WIND TUNNEL LABORATORIUM
AERODINAMIKA ITDA
Total View This Week0
Total View This Week0
Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Virgiawan Lesalli, Prytha
Subject
T Technology (General)
Datestamp
2024-07-19 08:27:47
Abstract :
Wind tunnel is kind of tunnel with determined air flow velocity for learn about the effect from object which is there is an airflow around it. The effect of that airflow can be a lift, drag dan and moment. Measuring instrument can be used to know the value about lift, drag and moment from the object. This research purposed for design and built measurement instrument to read lift, drag and pitching moment with load cell for knowing about the force reaction, data from sensors processed with amplifier and microcontroller Arduino Uno R3 with a data show in display 68x128 pixel. The accuracy test by experimental method by wind tunnel wit 30 cm x 30 cm test section, specimen used Clark-Y with 12 cm chord and 28 cm span, for knowing about lif, drag and moment coefficient with angle of attack Reynold numbers variation, value of error produced from difference from research and literature and divided with literature data. Literature data from Silverstein, A. (1935). Scale effect on Clark Y airfoil characteristics from NACA full-scale wind-tunnel tests. This instrument can be know the parameter wich is processed to be coefficient with mean accuracy from lift 4.5 % , drag 13% and momen coefficient from knowing arm of moment from specimen for 11.4%. This instrument use 3 load cell, which is 2 load cell (load cell A and B) for force reaction bounded in horisontal axis and connected with load cell C for read drag force reaction. Read for moment with looking for force support reaction and center force,mean first test error for Cl is 4.8 %, Cd is 8.5%, Cm is 9.2 %, mean second test for Cl is 4.9 %, Cd is 8 %, Cm is 8.7 %, mean third test for Cl is 4.2 %, Cd is 6.5 %, Cm is 6.6%. All mean test for Cl is 4.7 %, Cd is 7.6 %, Cm is 9.1 %.
Wind tunnel is kind of tunnel with determined air flow velocity for learn about the effect from object which is there is an airflow around it. The effect of that airflow can be a lift, drag dan and moment. Measuring instrument can be used to know the value about lift, drag and moment from the object. This research purposed for design and built measurement instrument to read lift, drag and pitching moment with load cell for knowing about the force reaction, data from sensors processed with amplifier and microcontroller Arduino Uno R3 with a data show in display 68x128 pixel. The accuracy test by experimental method by wind tunnel wit 30 cm x 30 cm test section, specimen used Clark-Y with 12 cm chord and 28 cm span, for knowing about lif, drag and moment coefficient with angle of attack Reynold numbers variation, value of error produced from difference from research and literature and divided with literature data. Literature data from Silverstein, A. (1935). Scale effect on Clark Y airfoil characteristics from NACA full-scale wind-tunnel tests. This instrument can be know the parameter wich is processed to be coefficient with mean accuracy from lift 4.5 % , drag 13% and momen coefficient from knowing arm of moment from specimen for 11.4%. This instrument use 3 load cell, which is 2 load cell (load cell A and B) for force reaction bounded in horisontal axis and connected with load cell C for read drag force reaction. Read for moment with looking for force support reaction and center force,mean first test error for Cl is 4.8 %, Cd is 8.5%, Cm is 9.2 %, mean second test for Cl is 4.9 %, Cd is 8 %, Cm is 8.7 %, mean third test for Cl is 4.2 %, Cd is 6.5 %, Cm is 6.6%. All mean test for Cl is 4.7 %, Cd is 7.6 %, Cm is 9.1 %.
Download
book
BibTex
Latex, Jabref
cloud_download
Original Resource
url resource Institution
