Design Open Circuit Wind Tunnels with Low Speed for Measuring the Lift Force that Act on The Wing Model
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Abstract
The objectives of this research were to build the open-circuit wind tunnel with a low speed that had a dimension of 18 inches wide, 65 inches long, and 18 inches high and to study the lift force of a wing of an airplane model by a sensor that installed in a wind tunnel. It was measured from force sensors installed inside the wind tunnel. The sensor system consisted of a strain gauge load cell that controlled force measurement and transformed the data using the Aduno program. As a result, the wind tunnel could do the test speed from 2 to 6 meters per second with the average total error of force measurement of 0.01 %. The result of the lift force that acted on the wing model showed that the lift force depended on the speed of the air flow through and the attack angle of the wing model. The range of the lift force form the highest to the least was NACA6409 9%, NACA4418, and NACA0021 respectively. Due to the NACA6409 9%, its wing had large curvature and less thickness compared to other types. For this reason, the pressure on the wing was less than pressure at the bottom of the wing. This resulted in the maximum lifting force applied to the wing. For the NACA 0021, the wing had the highest thickness and no curvature. These caused no difference in the pressure above and under the wing which resulted in the lift force that least done to the wing.
Article Details
บทความที่ได้รับการตีพิมพ์เป็นลิขสิทธิ์ของ วารสารวิทยาศาสตร์และเทคโนโลยี มหาวิทยาลัยอุบลราชธานี
ข้อความที่ปรากฏในบทความแต่ละเรื่องในวารสารวิชาการเล่มนี้เป็นความคิดเห็นส่วนตัวของผู้เขียนแต่ละท่านไม่เกี่ยวข้องกับมหาวิทยาลัยอุบลราชธานี และคณาจารย์ท่านอื่นๆในมหาวิทยาลัยฯ แต่อย่างใด ความรับผิดชอบองค์ประกอบทั้งหมดของบทความแต่ละเรื่องเป็นของผู้เขียนแต่ละท่าน หากมีความผิดพลาดใดๆ ผู้เขียนแต่ละท่านจะรับผิดชอบบทความของตนเองแต่ผู้เดียว
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