title: Ð¡ÑÐ°Ð²Ð½Ð¸ÑÐµÐ»ÑÐ½ÑÐ¹ Ð°Ð½Ð°Ð»Ð¸Ð· Ð°ÑÑÐ¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ñ Ñ Ð°ÑÐ°ÐºÑÐµÑÐ¸ÑÑÐ¸Ðº ÑÑÐ´Ð° ÐºÑÑÐ»Ð¾Ð²ÑÑ Ð¿ÑÐ¾ÑÐ¸Ð»ÐµÐ¹
title: Ð²ÑÐ¿ÑÑÐºÐ½Ð°Ñ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¾Ð½Ð½Ð°Ñ ÑÐ°Ð±Ð¾ÑÐ° Ð±Ð°ÐºÐ°Ð»Ð°Ð²ÑÐ°
titleType: Subtitle
title: Comparative analysis of the aerodynamic characteristics of a number of airfoils
Creators: name: ÐÐ¾ÑÑÐºÐ¸Ð½Ð°, Ð¯Ð½Ð°
Publisher: name: Ð¡Ð°Ð½ÐºÑ-ÐÐµÑÐµÑÐ±ÑÑÐ³ÑÐºÐ¸Ð¹ Ð¿Ð¾Ð»Ð¸ÑÐµÑÐ½Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ½Ð¸Ð²ÐµÑÑÐ¸ÑÐµÑ ÐÐµÑÑÐ° ÐÐµÐ»Ð¸ÐºÐ¾Ð³Ð¾
Year: 2022
Subjects: Ð°ÑÑÐ¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ð¹ Ð¿ÑÐ¾ÑÐ¸Ð»Ñ
Ð¾Ð¿ÑÐ¸Ð¼Ð¸Ð·Ð°ÑÐ¸Ñ
Ð¼ÐµÑÐ¾Ð´ ÑÐ¾Ð¿ÑÑÐ¶ÑÐ½Ð½Ð¾Ð³Ð¾ Ð³ÑÐ°Ð´Ð¸ÐµÐ½ÑÐ°
airfoil
optimisation
adjoint method
fluent

description: ÐÐ°ÑÑÐ¾ÑÑÐ°Ñ ÑÐ°Ð±Ð¾ÑÐ° Ð¿Ð¾ÑÐ²ÑÑÐµÐ½Ð° Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ñ ÑÐ²Ð¾Ð¹ÑÑÐ² Ð¾Ð¿ÑÐ¸Ð¼Ð¸Ð·Ð°ÑÐ¸Ð¸, Ð¿Ð¾Ð»ÑÑÐµÐ½Ð½Ð¾Ð¹ Ñ Ð¿Ð¾Ð¼Ð¾ÑÑÑ ÑÐ¾Ð¿ÑÑÐ¶ÑÐ½Ð½Ð¾Ð³Ð¾ ÑÐµÑÐ°ÑÐµÐ»Ñ, ÑÐµÐ°Ð»Ð¸Ð·Ð¾Ð²Ð°Ð½Ð½Ð¾Ð³Ð¾ Ð² Ð¿ÑÐ¾Ð¿ÑÐ¸ÐµÑÐ°ÑÐ½Ð¾Ð¼ Ð¿ÑÐ¾Ð³ÑÐ°Ð¼Ð¼Ð½Ð¾Ð¼ Ð¿Ð°ÐºÐµÑÐµ ANSYS Fluent 2019 R3, Ð½Ð° Ð¿ÑÐ¸Ð¼ÐµÑÐµ Ð´Ð²ÑÐ¼ÐµÑÐ½Ð¾Ð¹ Ð·Ð°Ð´Ð°ÑÐ¸ Ð¼Ð¾Ð´Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¸ Ð³ÐµÐ¾Ð¼ÐµÑÑÐ¸ÑÐµÑÐºÐ¾Ð¹ ÑÐ¾ÑÐ¼Ñ Ð´Ð²ÑÑ Ð°ÑÑÐ¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ñ Ð¿ÑÐ¾ÑÐ¸Ð»ÐµÐ¹ (ÑÐ¸Ð¼Ð¼ÐµÑÑÐ¸ÑÐ½Ð¾Ð³Ð¾ NACA 0012 Ð¸ Ð°ÑÐ¸Ð¼Ð¼ÐµÑÑÐ¸ÑÐ½Ð¾Ð³Ð¾ NACA 4412)Â  Ð¿ÑÐ¸ ÑÐ¸ÑÐ»Ðµ Ð ÐµÐ¹Ð½Ð¾Ð»ÑÐ´ÑÐ° Re = 6Â·106 Ð¸ ÑÐ°Ð·Ð»Ð¸ÑÐ½ÑÑ ÑÐ³Ð»Ð¾Ð² Ð°ÑÐ°ÐºÐ¸ Î± = 0Â°, 5Â°, 10Â° Ð´Ð»Ñ ÑÐ°Ð·Ð½ÑÑ Ð¾Ð±Ð»Ð°ÑÑÐµÐ¹ Ð¾Ð¿ÑÐ¸Ð¼Ð¸Ð·Ð°ÑÐ¸Ð¸. ÐÐ°Ð´Ð°ÑÐ¸, ÐºÐ¾ÑÐ¾ÑÑÐµ ÑÐµÑÐ°Ð»Ð¸ÑÑ Ð² ÑÐ¾Ð´Ðµ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ñ: 1. ÐÐ¾Ð´Ð³Ð¾ÑÐ¾Ð²ÐºÐ° ÑÐ°ÑÑÑÑÐ½Ð¾Ð¹ Ð¿Ð¾ÑÑÐ°Ð½Ð¾Ð²ÐºÐ¸ Ð·Ð°Ð´Ð°ÑÐ¸ Ð´Ð»Ñ Ð³Ð¸Ð´ÑÐ¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¾Ð³Ð¾ ÑÐ¾Ð»Ð²ÐµÑÐ° ANSYS Fluent, ÐµÑ ÑÐµÑÐµÐ½Ð¸Ðµ Ð¸ Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½Ð¸Ðµ Ð¼ÐµÑÐ¾Ð´Ð¸ÑÐµÑÐºÐ¸Ñ ÑÐ°ÑÑÑÑÐ¾Ð². 2. ÐÐ°Ð»Ð¸Ð´Ð°ÑÐ¸Ñ ÑÐ°Ð·ÑÐ°Ð±Ð¾ÑÐ°Ð½Ð½Ð¾Ð¹ ÑÐ¸ÑÐ»ÐµÐ½Ð½Ð¾Ð¹ Ð¼Ð¾Ð´ÐµÐ»Ð¸, ÑÐ¾Ð¿Ð¾ÑÑÐ°Ð²Ð»ÐµÐ½Ð¸Ðµ Ð¿Ð¾Ð»ÑÑÐµÐ½Ð½ÑÑ ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÐ¾Ð² Ñ ÑÑÐ°Ð»Ð¾Ð½Ð½ÑÐ¼Ð¸ Ð¸ ÑÐºÑÐ¿ÐµÑÐ¸Ð¼ÐµÐ½ÑÐ°Ð»ÑÐ½ÑÐ¼Ð¸ Ð·Ð½Ð°ÑÐµÐ½Ð¸ÑÐ¼Ð¸. 3. ÐÐ¾Ð´Ð³Ð¾ÑÐ¾Ð²ÐºÐ° ÑÐ°ÑÑÑÑÐ½Ð¾Ð¹ Ð¿Ð¾ÑÑÐ°Ð½Ð¾Ð²ÐºÐ¸ Ð·Ð°Ð´Ð°ÑÐ¸ Ð´Ð»Ñ ÑÐ¾Ð¿ÑÑÐ¶ÑÐ½Ð½Ð¾Ð³Ð¾ ÑÐ¾Ð»Ð²ÐµÑÐ° ANSYS Fluent Ð¸ Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½Ð¸Ðµ ÑÐ°ÑÑÑÑÐ¾Ð² Ð´Ð»Ñ Ð²ÑÐµÑ ÑÐ»ÑÑÐ°ÐµÐ² Ð¾Ð¿ÑÐ¸Ð¼Ð¸Ð·Ð°ÑÐ¸Ð¸. 4. ÐÑÐ±Ð¾Ñ Ð½ÐµÑÐºÐ¾Ð»ÑÐºÐ¸Ñ Ð¿ÑÐ¾ÑÐ¸Ð»ÐµÐ¹, Ð¿Ð¾Ð»ÑÑÐµÐ½Ð½ÑÑ Ð² ÑÐ¾Ð´Ðµ Ð¼Ð¾Ð´Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¸, Ð¸ Ð´Ð°Ð»ÑÐ½ÐµÐ¹ÑÐµÐµ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ðµ Ð¸Ñ Ð°ÑÑÐ¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ñ ÑÐ°ÑÐ°ÐºÑÐµÑÐ¸ÑÑÐ¸Ðº Ð² ÑÑÐ°Ð²Ð½ÐµÐ½Ð¸Ð¸ Ñ Ð¸ÑÑÐ¾Ð´Ð½ÑÐ¼Ð¸. Ð ÑÐ¾Ð´Ðµ Ð²ÑÐ¿Ð¾Ð»Ð½ÐµÐ½Ð¸Ñ ÑÐ°Ð±Ð¾ÑÑ Ð±ÑÐ»Ð° Ð¿Ð¾Ð´Ð³Ð¾ÑÐ¾Ð²Ð»ÐµÐ½Ð° ÑÐ°ÑÑÑÑÐ½Ð°Ñ Ð¿Ð¾ÑÑÐ°Ð½Ð¾Ð²ÐºÐ° Ð´Ð²ÑÐ¼ÐµÑÐ½Ð¾Ð¹ Ð·Ð°Ð´Ð°ÑÐ¸ Ð¾Ð± Ð¾Ð±ÑÐµÐºÐ°Ð½Ð¸Ð¸ Ð±ÐµÑÐºÐ¾Ð½ÐµÑÐ½ÑÐ¼ ÑÑÐ°ÑÐ¸Ð¾Ð½Ð°ÑÐ½ÑÐ¼ ÑÑÑÐ±ÑÐ»ÐµÐ½ÑÐ½ÑÐ¼ Ð¸Ð·Ð¾ÑÐµÑÐ¼Ð¸ÑÐµÑÐºÐ¸Ð¼ ÑÐµÑÐµÐ½Ð¸ÐµÐ¼ Ð½ÐµÑÐ¶Ð¸Ð¼Ð°ÐµÐ¼Ð¾Ð³Ð¾ Ð³Ð°Ð·Ð° (Ð²Ð¾Ð·Ð´ÑÑÐ°) Ð°ÑÑÐ¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¾Ð³Ð¾ Ð¿ÑÐ¾ÑÐ¸Ð»Ñ Ð¸ Ð¾ÑÑÑÐµÑÑÐ²Ð»ÐµÐ½Ð° ÐµÑ Ð²Ð°Ð»Ð¸Ð´Ð°ÑÐ¸Ñ. Ð ÑÐ¾Ð´Ðµ ÐµÑ ÑÐµÐ°Ð»Ð¸Ð·Ð°ÑÐ¸Ð¸ Ð±ÑÐ»Ð¸ Ð¿ÑÐ¾Ð²ÐµÐ´ÐµÐ½Ñ Ð¼ÐµÑÐ¾Ð´Ð¸ÑÐµÑÐºÐ¸Ðµ ÑÐ°ÑÑÑÑÑ, Ð²ÐºÐ»ÑÑÐ°ÑÑÐ¸Ðµ Ð² ÑÐµÐ±Ñ Ð¿Ð¾Ð»ÑÑÐµÐ½Ð¸Ðµ ÑÐµÑÐ¾ÑÐ½Ð¾Ð³Ð¾-Ð½ÐµÐ·Ð°Ð²Ð¸ÑÐ¸Ð¼Ð¾Ð³Ð¾ ÑÐµÑÐµÐ½Ð¸Ñ, Ð° ÑÐ°ÐºÐ¶Ðµ ÑÑÐ°Ð²Ð½ÐµÐ½Ð¸Ðµ Ð¿Ð¾Ð»ÑÑÐµÐ½Ð½ÑÑ ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÐ¾Ð² Ñ ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÐ°Ð¼Ð¸ Ð´ÑÑÐ³Ð¸Ñ CFD ÐºÐ¾Ð´Ð¾Ð² Ð¸ ÑÐºÑÐ¿ÐµÑÐ¸Ð¼ÐµÐ½ÑÐ°Ð»ÑÐ½ÑÐ¼Ð¸ Ð´Ð°Ð½Ð½ÑÐ¼Ð¸. ÐÑÐ»Ð° Ð¿Ð¾Ð´Ð³Ð¾ÑÐ¾Ð²Ð»ÐµÐ½Ð° Ð¸ Ð¿ÑÐ¾Ð²ÐµÐ´ÐµÐ½Ð° Ð¼Ð¾Ð´Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ñ Ð³ÐµÐ¾Ð¼ÐµÑÑÐ¸ÑÐµÑÐºÐ¾Ð¹ ÑÐ¾ÑÐ¼Ñ Ð´Ð»Ñ Ð¿ÑÐ¾ÑÐ¸Ð»ÐµÐ¹ NACA 0012 Ð¸ NACA 4412 Ð´Ð»Ñ ÑÐ°Ð·Ð½ÑÑ Ð¾Ð±Ð»Ð°ÑÑÐµÐ¹ Ð¾Ð¿ÑÐ¸Ð¼Ð¸Ð·Ð°ÑÐ¸Ð¸ Ð¸ Ð¿ÑÐ¸ ÑÐ°Ð·Ð»Ð¸ÑÐ½ÑÑ ÑÐ³Ð»Ð°Ñ Ð°ÑÐ°ÐºÐ¸, Ð¿Ð¾ ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÐ°Ð¼ ÐºÐ¾ÑÐ¾ÑÐ¾Ð¹ Ð±ÑÐ»Ð¸ Ð²ÑÐ±ÑÐ°Ð½Ñ ÑÐµÑÑÑÐµ Ð¼Ð¾Ð´Ð¸ÑÐ¸ÑÐ¸ÑÐ¾Ð²Ð°Ð½Ð½ÑÑ ÐºÑÑÐ»Ð¾Ð²ÑÑ Ð¿ÑÐ¾ÑÐ¸Ð»Ñ, Ð°ÑÑÐ¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ðµ ÑÐ°ÑÐ°ÐºÑÐµÑÐ¸ÑÑÐ¸ÐºÐ¸ ÐºÐ¾ÑÐ¾ÑÑÑ Ð±ÑÐ»Ð¸ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ñ Ð¿ÑÐ¸ ÑÐ°Ð·Ð»Ð¸ÑÐ½ÑÑ ÑÐ³Ð»Ð°Ñ Ð°ÑÐ°ÐºÐ¸ Ð² ÑÑÐ°Ð²Ð½ÐµÐ½Ð¸Ð¸ Ñ Ð¸ÑÑÐ¾Ð´Ð½ÑÐ¼Ð¸. ÐÐ½Ð°Ð»Ð¸Ð· Ð¿ÑÐ¾Ð²Ð¾Ð´Ð¸Ð»ÑÑ Ð¼ÐµÑÐ¾Ð´Ð¾Ð¼ Ð¼Ð°ÑÐµÐ¼Ð°ÑÐ¸ÑÐµÑÐºÐ¾Ð³Ð¾ Ð¼Ð¾Ð´ÐµÐ»Ð¸ÑÐ¾Ð²Ð°Ð½Ð¸Ñ Ñ Ð¸ÑÐ¿Ð¾Ð»ÑÐ·Ð¾Ð²Ð°Ð½Ð¸ÐµÐ¼ Ð¿ÑÐ¾Ð¿ÑÐ¸ÐµÑÐ°ÑÐ½Ð¾Ð³Ð¾ Ð¿ÑÐ¾Ð³ÑÐ°Ð¼Ð¼Ð½Ð¾Ð³Ð¾ Ð¾Ð±ÐµÑÐ¿ÐµÑÐµÐ½Ð¸Ñ ANSYS Fluent 2019 R3, Ð² ÐºÐ¾ÑÐ¾ÑÐ¾Ð¼ ÑÐµÐ°Ð»Ð¸Ð·Ð¾Ð²Ð°Ð½Ñ Ð³Ð¸Ð´ÑÐ¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ðµ Ð¸ ÑÐ¾Ð¿ÑÑÐ¶ÑÐ½Ð½ÑÐ¹ ÑÐ¾Ð»Ð²ÐµÑÑ. Ð ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÐµ Ð±ÑÐ»Ð¸ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ñ ÑÐ²Ð¾Ð¹ÑÑÐ²Ð° Ð¾Ð¿ÑÐ¸Ð¼Ð¸Ð·Ð°ÑÐ¸Ð¸, Ð¿Ð¾Ð»ÑÑÐµÐ½Ð½Ð¾Ð¹ Ñ Ð¿Ð¾Ð¼Ð¾ÑÑÑ ÑÐ¾Ð¿ÑÑÐ¶ÑÐ½Ð½Ð¾Ð³Ð¾ ÑÐµÑÐ°ÑÐµÐ»Ñ, ÑÐµÐ°Ð»Ð¸Ð·Ð¾Ð²Ð°Ð½Ð½Ð¾Ð³Ð¾ Ð² Ð¿ÑÐ¾Ð³ÑÐ°Ð¼Ð¼Ð½Ð¾Ð¼ Ð¿Ð°ÐºÐµÑÐµ ANSYS Fluent, Ð½Ð° Ð¿ÑÐ¸Ð¼ÐµÑÐµ Ð´Ð²ÑÐ¼ÐµÑÐ½Ð¾Ð¹ Ð·Ð°Ð´Ð°ÑÐ¸ Ð¼Ð¾Ð´Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¸ Ð³ÐµÐ¾Ð¼ÐµÑÑÐ¸ÑÐµÑÐºÐ¾Ð¹ ÑÐ¾ÑÐ¼Ñ Ð´Ð²ÑÑ Ð°ÑÑÐ¾Ð´Ð¸Ð½Ð°Ð¼Ð¸ÑÐµÑÐºÐ¸Ñ Ð¿ÑÐ¾ÑÐ¸Ð»ÐµÐ¹. ÐÐ° Ð¾ÑÐ½Ð¾Ð²Ð°Ð½Ð¸Ð¸ ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÐ¾Ð² Ð´Ð°Ð½Ð½Ð¾Ð³Ð¾ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ñ Ð±ÑÐ» Ð¿Ð¾Ð»ÑÑÐµÐ½ Ð²ÑÐ²Ð¾Ð´ Ð¾ ÑÐ¾Ð¼, ÑÑÐ¾ Ð¸ÑÐ¿Ð¾Ð»ÑÐ·Ð¾Ð²Ð°Ð½Ð¸Ðµ ÑÐ¾Ð¿ÑÑÐ¶ÑÐ½Ð½Ð¾Ð³Ð¾ ÑÐ¾Ð»Ð²ÐµÑÐ° ÑÑÐµÐ±ÑÐµÑ ÑÑÐ°ÑÐµÐ»ÑÐ½Ð¾Ð³Ð¾ Ð¸ Ð°ÐºÐºÑÑÐ°ÑÐ½Ð¾Ð³Ð¾ Ð²ÑÐ±Ð¾ÑÐ° Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÐ¾Ð² Ð¾Ð¿ÑÐ¸Ð¼Ð¸Ð·Ð°ÑÐ¸Ð¸, Ñ.Ðº. Ð¸Ð¼ÐµÑÑ Ð¼ÐµÑÑÐ¾ Ð¾ÑÐ¾Ð±ÐµÐ½Ð½Ð¾ÑÑÐ¸, ÐºÐ¾ÑÐ¾ÑÑÐµ Ð¼Ð¾Ð³ÑÑ Ð¿Ð¾Ð½Ð¸Ð·Ð¸ÑÑ ÐºÐ°ÑÐµÑÑÐ²Ð¾ Ð¿ÑÐ¾Ð²Ð¾Ð´Ð¸Ð¼Ð¾Ð¹ Ð¼Ð¾Ð´Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¸. Ð¢Ð°ÐºÐ¸Ð¼ Ð¾Ð±ÑÐ°Ð·Ð¾Ð¼, Ð¿ÑÐ¸ Ð¾Ð¿ÑÐ¸Ð¼Ð¸Ð·Ð°ÑÐ¸Ð¸ Ð¿Ð¾Ð´Ð¾Ð±Ð½Ð¾Ð¹ Ð·Ð°Ð´Ð°ÑÐ¸ ÑÑÐ¾Ð¸Ñ ÑÑÐ¸ÑÑÐ²Ð°ÑÑ Ð´Ð°Ð½Ð½ÑÐµ ÑÐ²Ð¾Ð¹ÑÑÐ²Ð° ÑÐµÑÐ°ÑÐµÐ»Ñ, Ð¸ Ð¿ÑÐ¸ Ð½ÐµÐ¾Ð±ÑÐ¾Ð´Ð¸Ð¼Ð¾ÑÑÐ¸ Ð¸Ð·Ð¼ÐµÐ½ÑÑÑ Ð¿Ð°ÑÐ°Ð¼ÐµÑÑÑ Ð¼Ð¾Ð´Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¸.
description: The given work is devoted to studying optimization properties obtained using the adjoint solver implemented in the proprietary software package ANSYS Fluent 2019 R3, using the example of a two-dimensional problem of modifying the geometric shape of two airfoils (symmetric NACA 0012 and asymmetric NACA 4412) at Reynolds number Re = 6Â·106 and different angles of attack Î± = 0Â°, 5Â°, 10Â° for different control volumes of optimization.The research set the following goals: 1. Preparation of the computational statement of the problem for the ANSYS Fluent hydrodynamic solver, its solution and the performance of methodical calculations. 2. Validation of the developed numerical model, comparison of the obtained results with reference and experimental values. 3. Preparation of a computational problem statement for the coupled ANSYS Fluent solver and performing calculations for all optimization cases. 4. Selection of several profiles obtained during the modification, and further study of their aerodynamic characteristics in comparison with the original ones.In the process of performing the work, a computational formulation of a two-dimensional problem of an infinite stationary turbulent isothermal flow around an incompressible gas (air) of an airfoil was prepared and validated. In the course of its implementation, methodical calculations were carried out, including obtaining a grid-independent solution, as well as comparing the results obtained with the results of other CFD codes and experimental data. A modification of the geometric shape for the NACA 0012 and NACA 4412 airfoils was prepared and carried out for different control volumes of optimization and at different angles of attack, as a result of which four modified airfoils were selected, the aerodynamic characteristics of which were studied at different angles of attack in comparison with the initial ones. The analysis was carried out by mathematical modeling using proprietary software ANSYS Fluent 2019 R3, which implements hydrodynamic and conjugate solvers. As a result, the optimization properties obtained with the help of an adjoint solver implemented in the ANSYS Fluent software package were studied using the example of a two-dimensional problem of modifying the geometric shape of two airfoils. Based on the results of this study, it was concluded that the use of a conjugate solver requires a careful and accurate choice of optimization parameters, since there are features that can reduce the quality of the modification. Thus, when optimizing such a problem, it is worth considering these properties of the solver and, if necessary, changing the modification parameters.