서울대학교 빅데이터 지식정보플랫폼
전체 메뉴
AI 검색
최근 확인한 콘텐츠
3건 더보기
loading...
반출리포트 생성
논문 목록
Investigation of drag reduction performance of half NACA 0009 and 0012 airfoils placed over a trailer on the flow around truck-trailer
저자
Mehmet Seyhan, Mustafa Sarioglu
학술지명
Journal of Mechanical Science and Technology
출판/발행연도
2021
주제
요약
본 연구는 트레일러에 부착된 반 에어포일과 지붕 페어링의 공력 저항 감소 성능을 풍동 실험을 통해 조사했습니다. 반 에어포일(NACA 0009, NACA 0012)과 지붕 페어링 위치 변화에 따른 성능을 분석한 결과, 반 에어포일 단독 사용 시 최대 10%의 공력 저항 감소 효과를 보였으며, 반 에어포일과 지붕 페어링을 함께 사용했을 때는 30% 이상의 감소 효과를 확인했습니다.
연관 콘텐츠
LikeSNU에서 의미기반으로 분석하여 연관된 자료를 추천해드립니다.
-
Wind - tunnel investigation of drooped ailerons on a 16 - percent - thick low - drag airfoil
-
Comparison of the experimental pressure distribution on an NACA 0012 profile at high speeds with that calculated by the relaxation method
-
High - speed tests of an airfoil section cambered to have critical mach numbers higher than those attainable with a uniform - load mean line
-
Low - speed characteristics of four cambered, 10 - percent - thick NACA airfoil sections
-
Wind - tunnel investigation of effects of various aerodynamic balance shapes and sweepback on control - surface characteristics of semispan tail surfaces with NACA 0009, 0015, 66-009, 66(215)-014, and circular - arc airfoil sections
-
Comparative drag measurements at transonic speeds of rectangular and sweptback NACA 65 - 009 airfoils mounted on a freely falling body
-
Aerodynamic characteristics of a number of modified NACA four - digit - series airfoil sections
-
Pressure - distribution investigation of an N.A.C.A. 0009 airfoil with a 50 - percent - chord plain flap and three tabs
-
Chordwise and spanwise loadings measured at low speed on a triangular wing having an aspect ratio of two and an NACA 0012 airfoil section
-
The development of cambered airfoil sections having favorable lift characteristics at supercritical mach numbers
-
Low Reynolds number aerodynamics : proceedings of the conference, Notre Dame, Indiana, USA, 5-7 June 1989
-
Wind - tunnel investigation of effects of forward movements of transition on section characteristics of a low - drag airfoil with a 0.24 - chord sealed plain aileron
-
Exploratory wind - tunnel investigation of the effectiveness of area suction in eliminating leading - edge separation over an NACA 64 1A212 airfoil
-
Two - dimensional wind - tunnel investigation of an NACA 64-009 airfoil equipped with two types of leading - edge flap
-
Pressure - distribution investigation of an N.A.C.A. 0009 airfoil with an 80- percent - chord plain flap and three tabs
-
Effect of compressibility on the distribution of pressure over a tapered wing of NACA 230-series airfoil sections
-
Low - speed experimental investigation of a thin, faired, double - wedge airfoil section with nose and trailing - edge flaps
-
Investigation of boundary - layer control to improve the lift and drag characteristics of the NACA 65 2 - 415 airfoil section with double slotted and plain flaps
-
Subsonic two - dimensional - flow conditions near an airfoil determined by static pressures measured at the tunnel wall
-
Two - dimensional wind - tunnel investigation of the NACA 64 1-012 airfoil equipped with two types of leading - edge flap
이전
다음
이전
다음
이전
다음