Dataset of the twin floater of amphibian aircraft in wind tunnel test

被引：0

作者：

Karyawan ^{[1
,6
]}

Suwasono, Bagiyo ^{[2
]}

Supartono ^{[2
]}

Syamsuar, Sayuti ^{[3
]}

Muharam, Aam ^{[3
]}

Widyawasta ^{[4
]}

Pane, Ivransa Zuhdi ^{[1
]}

Haryanto, Ismoyo ^{[5
]}

Tauviqirrahman, Mohammad ^{[5
]}

Yohana, Eflita ^{[5
]}

机构：

[1] Natl Res & Innovat Agcy, Aerodynam Aeroelast & Aeroacoust Lab, KST BJ Habibie, Banten 15314, Indonesia

[2] Hang Tuah Univ, Postgrad Program Marine Technol, Surabaya 60111, East Java, Indonesia

[3] Natl Res & Innovat Agcy, Res Ctr Transportat Technol, KST BJ Habibie, South Tangerang 15314, Banten, Indonesia

[4] Natl Res & Innovat Agcy, Res Ctr Aviat Technol, KST BJ Habibie, Banten 15314, Indonesia

[5] Diponegoro Univ, Dept Mech Engn, Semarang, Indonesia

[6] Diponegoro Univ, Dept Mech, Semarang, Indonesia

来源：

DATA IN BRIEF | 2024年 / 57卷

关键词：

Twin floater; Flap; Lift coefficient; Drag coefficient; Wind tunnel test;

D O I：

10.1016/j.dib.2024.111008

中图分类号：

O [数理科学和化学]; P [天文学、地球科学]; Q [生物科学]; N [自然科学总论];

学科分类号：

07 ; 0710 ; 09 ;

摘要：

It is well known that seaplanes have twin floaters. Therefore, it is necessary to conduct a wind tunnel test that aims to determine the performance of twin floaters paired on a mock aircraft model. The twin floaters use the same scale as the mock aircraft, which is 1:6.3 with a length of 1555 mm and a distance between floaters of 668.8 mm or S/L of 0.43. The test plan uses a speed of 65 m s(-1) and a Reynolds number 1.5 times the model configuration with flap angle variations of 0 degrees, 10 degrees, 18 degrees, 30 degrees, and 40 degrees. The final test results showed that tabulations and graphs of lift coefficient (C-L), drag coefficient (C-D), and pitching moment coefficient (C-M) with angle of attack (alpha) variations of -10 degrees to 16 degrees. (c) 2024 The Author(s). Published by Elsevier Inc. This is an open access article under the CC BY-NC license ( http://creativecommons.org/licenses/by-nc/4.0/ )

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页数：15

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