IMPROVEMENT OF AERODYNAMIC PERFORMANCE OF AN AIRCRAFT USING MORPHING WING
IMPROVEMENT OF AERODYNAMIC PERFORMANCE OF AN AIRCRAFT USING MORPHING WING
The aerodynamic performance of an aircraft directly affects the operating cost of the aircraft. The aerodynamic performance can be defined as the Cl/Cd ratio. To decrease operating cost Cl/Cd ratio must be increased. The main factor affecting the Cl/Cd ratio is the airfoil. Hence in this study, focused on a morphing airfoil during the flight to obtain maximum Cl/Cd ratio at a various angle of attack values. 2D CFD analysis is used in this study based on NACA63-215 airfoil and a new NACA36-215_1 airfoil which is modified NACA63-215. In analyses Cl/Cd ratio and flow separation were investigated as the performance parameters. At the end of the study, it was seen that the NACA63-215 airfoil should be used between 110-170 angle of attack, NACA63-215_1 should be used between 00-100, 180-230 angle of attack, to obtain maximum performance.
Keywords:
Morphing Airfoil flow separation, lift coefficient, drag coefficient,
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- ISSN: 2602-294X
- Yayın Aralığı: Yılda 2 Sayı
- Başlangıç: 2016
- Yayıncı: Gaziantep Üniversitesi
Sayıdaki Diğer Makaleler
INVESTIGATION OF TOTAL CARBON AND NITROGEN CONTENT OF GAZİANTEP AGRICULTURAL SOILS
IMPROVEMENT OF AERODYNAMIC PERFORMANCE OF AN AIRCRAFT USING MORPHING WING
İbrahim GÖV, Mehmet Hanifi DOĞRU, Ümit KORKMAZ
EXHAUST FLUE GAS HEAT RECOVERY POTENTIAL OF HEATING BOILERS OF BUILDINGS
COMPARISON OF HEXAGONAL, SQUARE AND CIRCULAR SECTIONED HONEYCOMB PERFORMANCE IN A WIND TUNNEL
COMPARISON OF SQUARE AND CIRCULAR SECTIONED WIND TUNNEL PERFORMANCE