Drag polar analysis for a flying car model using wind tunnel test method

Kayshara Fadillo Lubyana, Mohammad Adhitya

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

Abstract

Traffic has been one of major problems for big cities all around the globe. There are multiple causes of traffic congestion, as too many cars for the roadway due to inadequate mass transit options, a blockage and merger on the road as obstacles for traffic flow such as road work or lane closure due to utility work, or an accident, traffic signals out of sync, pedestrians crossing not permitting cars to turn, and overdevelopment in areas where the mass transit system is already overcrowded and the road system is inadequate. Traffic has the domino effects to some of other problems, like productivity, as the time spent on the road doing nothing productive is increasing means less productive results; pollution, because the longer time on the road mena smore fuel is burnt thus more pollution; and many more. There is one solution offered, that several companies in the world have created but still under development. That one solution is flying car. This idea was actually popular in 1926, the obsession of vehicle that could fly. After a long postpone, this idea is created to reality by several companies like Aeromobil and AeroCar. As one of the most prestigious University in Indonesia, Universitas Indonesia through its own Advanced Vehicle Research Center could also take part in the development of the flying car. This thesis covers entirely about polar diagram, as an illustration for the ratio of lift coefficient (CL) and drag coefficient (CD). The model is created in the size of 1/7 real size, tested with a wind tunnel. The maximum value of this comparison is a crucial number for the determination of the overall design. The values are collected based on the wind tunnel testing. This research is a quantitative type with descriptive design. The polar diagram analysis shows that the maximum value of the ratio is 7.449 at 12o of angle of attack. With the value of maximum lift-to-drag ratio, the thrust required for steady level flight is calculated. The thrust required with analytical approach reaches 1 702.246 N and the graphical approach result is 33.823 N.

Original languageEnglish
Title of host publicationRecent Progress on
Subtitle of host publicationMechanical, Infrastructure and Industrial Engineering - Proceedings of the International Symposium on Advances in Mechanical Engineering, ISAME 2019: Quality in Research 2019
Editors Nahry, Dwinanti Rika Marthanty
PublisherAmerican Institute of Physics Inc.
ISBN (Electronic)9780735419865
DOIs
Publication statusPublished - 6 May 2020
Event16th International Conference on Quality in Research, QiR 2019 - 2019 International Symposium on Advances in Mechanical Engineering, ISAME 2019 - Padang, Indonesia
Duration: 22 Jul 201924 Jul 2019

Publication series

NameAIP Conference Proceedings
Volume2227
ISSN (Print)0094-243X
ISSN (Electronic)1551-7616

Conference

Conference16th International Conference on Quality in Research, QiR 2019 - 2019 International Symposium on Advances in Mechanical Engineering, ISAME 2019
Country/TerritoryIndonesia
CityPadang
Period22/07/1924/07/19

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