Investigation of Air Flow Over Delta and Cranked Arrow Delta Wings. (Dept. M.)

Abstract

Delta wing shapes are unique in their structure advantages and aerodynamic characteristics. On supersonic designing, a delta wing shape is often used to reduce drag and achieve the optimal performance. In this study, a commercial software (ANSYS 15) is used to investigate the performance of two delta wing shapes (simple delta wing and cranked arrow delta wing) at different angles of attack (5° to 65°) and different flow speeds (M = 0.15 to 1.4) in order to obtain the lift and drag coefficients, pressure distribution around the investigated wings, and velocity filed. The results indicate that: (i) at subsonic speed (M = 0.15 to 0.8), the lift coefficient for the cranked arrow delta wing increases by about 25%. While the drag coefficient in case of cranked arrow delta wing increases by a value reaches 5%, as the area of the cranked arrow delta wing is less by about 7%, this leads to decreasing drag force for the cranked arrow wing, which improves its performance. The lift and drag coefficients increase A. M. Draz is a mechanical power engineer (eahmeddraz@gmail.com). H. M. El Saadany, Professor at Mechanical Power Engineering Department. Faculty of Engineering, Mansoura University, (Hmsaadny@yahoo.com). with increasing Mach number, the rate of increase is higher in the cranked arrow delta wing. In cranked arrow delta wing, vortex breakdown is delayed than that in simple delta wing, which makes the cranked arrow more stable. In addition, the cut parts from cranked arrow at trailing edge help to avoid the effect of vortex breakdown on the wing. (ii) At supersonic speed (M = 1.2 to M = 1.4), the lift coefficient of the cranked arrow delta wing is higher than that for simple delta wing by about 15%, while the increase in the drag coefficient does not exceed 2%, which increases cranked arrow wing's performance. The lift and drag coefficients decrease with increasing Mach number, the rate of decrease is higher in the cranked arrow delta wing. In the cranked arrow delta wing as Mach number increases, a better pressure distribution over the wing surface is observed which improves the stability during flight and maneuvering. ‫العربي‬ ‫الملخص‬ ‫دراس‬ ‫البحث‬ ‫لنا‬ ‫يقدم‬ : ‫ة‬ ‫عددي‬ ‫ة‬ ‫الحسابيه‬ ‫الموائع‬ ‫ميكانيكا‬ ‫برنامج‬ ‫باستخدام‬ (ANSYS 15 ‫لمقارن‬) ‫ة‬ ‫من‬ ‫شكلين‬ ‫أ‬ ‫ال‬ ‫شكال‬ ‫جنح‬ ‫ة‬ ‫المثلث‬ ‫ة‬ ‫وه‬ ‫ي‬ ‫المنكسر‬ ‫الدلتا‬ ‫جناح‬ ‫شكل‬ ‫و‬ ‫البسيط‬ ‫الدلتا‬ ‫شكل‬ ‫ال‬ ‫الدراس‬ ‫تمت‬ .‫ضالع‬ ‫ة‬ ‫ف‬ ‫ي‬ ‫من‬ ‫هجوم‬ ‫زوايا‬ ‫مدى‬ 5 ° ‫إ‬ ‫لى‬ 65 ° (‫بين‬ ‫يتراوح‬ ‫ماخ‬ ‫رقم‬ ‫عند‬ 0.15 ‫إ‬ ‫لى‬ 1.4 .) ‫و‬ ‫أ‬ ‫النتائج‬ ‫وضحت‬ ‫أ‬ ‫ف‬ ‫نه‬ ‫ي‬ ‫حال‬ ‫ة‬ ‫ال‬ ‫السرعات‬ ‫سرع‬ ‫من‬ ‫قل‬ ‫ة‬ ‫من‬ ‫ماخ‬ ‫(رقم‬ ‫الصوت‬ 0.15 ‫إ‬ ‫لى‬ 0.8) ‫أ‬ ‫الرفع‬ ‫معامل‬ ‫ن‬ (L C) ‫بنحو‬ ‫يزداد‬ 25 ‫ف‬ % ‫ي‬ ‫حال‬ ‫ة‬ ‫مقارن‬ ‫المنكسر‬ ‫الجناح‬ ‫ة‬ ‫ف‬ ‫البسيط‬ ‫بالجناح‬ ‫ي‬ ‫ال‬ ‫قوى‬ ‫تتناقص‬ ‫حين‬ ‫لسطح‬ ‫عاقه‬ ‫نتيج‬ ‫المنكسر‬ ‫الجناح‬ ‫ة‬ ‫ف‬ ‫للنقص‬ ‫ي‬ ‫بمقدار‬ ‫مساحته‬ 7 .% ‫وف‬ ‫ي‬ ‫حال‬ ‫ة‬ ‫ال‬ ‫السرعات‬ ‫سرع‬ ‫من‬ ‫على‬ ‫ة‬ ‫(رقم‬ ‫الصوت‬ ‫ماخ‬ 1.2 , 1.4 ‫ف‬) ‫إ‬ ‫الرفع‬ ‫معامل‬ ‫ن‬ (L C) ‫بمقدار‬ ‫يزداد‬ ‫حوال‬ ‫ي‬ 15 ‫ف‬ % ‫ي‬ ‫حال‬ ‫ة‬ ‫ال‬ ‫ج‬ ‫بالمقارن‬ ‫المنكسر‬ ‫ناح‬ ‫ة‬ ‫بال‬ ‫ج‬ ‫ناح‬ ‫زياد‬ ‫مقابل‬ ‫البسيط‬ ‫ة‬ ‫ف‬ ‫ي‬ ‫ال‬ ‫معامل‬ (‫عاقه‬ D C ‫ل‬ ‫بمقدار‬) ‫يتعدى‬ 2 ‫ف‬ .% ‫ي‬ ‫زياد‬ ‫الشكلين‬ ‫كال‬ ‫ة‬ ‫يؤد‬ ‫ماخ‬ ‫رقم‬ ‫ي‬ ‫إ‬ ‫لى‬ ‫زياد‬ ‫ة‬ ‫ف‬ ‫الرفع‬ ‫معامل‬ ‫ي‬ ‫حال‬ ‫ة‬ ‫ال‬ ‫السرعات‬ ‫سرع‬ ‫من‬ ‫قل‬ ‫ة‬ ‫الصوت‬ ‫ف‬ ‫وتناقص‬ ‫ي‬ ‫ال‬ ‫السرعات‬ ‫عند‬ ‫الرفع‬ ‫معامل‬ ‫على‬ ‫سرع‬ ‫من‬ ‫ة‬ .‫الصوت‬ ‫يزدا‬ ‫التغير‬ ‫ومعدل‬ ‫ف‬ ‫د‬ ‫ي‬ ‫حال‬ ‫ة‬ .‫المنكسر‬ ‫الجناح‬ ‫ف‬ ‫وكذلك‬ ‫إ‬ ‫ال‬ ‫سطح‬ ‫على‬ ‫الضغوط‬ ‫توزيع‬ ‫ن‬ ‫ج‬ ‫ناح‬ ‫المنكسر‬ ‫أ‬ ‫انتظاما‬ ‫كثر‬ ‫أن‬ ‫يتضح‬ ‫ذلك‬ ‫ومن‬. ‫أ‬ ‫الجناح‬ ‫داء‬ ‫المنكسر‬ ‫أ‬ ‫من‬ ‫فضل‬ ‫أ‬ ‫الجناح‬ ‫داء‬ ‫يعطيه‬ ‫مما‬ ‫البسيط‬ ‫أ‬ ‫فضلي‬ ‫ة‬ ‫ف‬ ‫ي‬ ‫حال‬ ‫ة‬ ‫والمناور‬ ‫الطيران‬ ‫ة‬. M: 2 A. M. DRAZ, H. M. EL SAADANY, M. M. AWAD AND W. M. EL AWADY