Tham khảo tài liệu 'a development of novel integral method for prediction of distorted inlet flow propagation_3', kỹ thuật - công nghệ, điện - điện tử phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | Results and Discussion 97 I _ OI CÙ 0 10 20 30 40 50 60 70 0o Fig. . The computed compressor static pressure rise versus inlet flow angle In the small and medium inlet flow angles the static pressure rises are almost the same with a constant value as shown in Fig. . The static pressure rise does not change whatever the inlet distorted velocity coefficient a 0 and the inlet size of distorted region ệ 0 are. However with a larger inlet flow angle 0O 45 the static pressure rises sharply with a higher inlet distorted velocity coefficient. By keeping eyes on the smaller inlet flow angles with 0 g 25 and changing a 0 from 0 to we can obtain the compressor characteristics as summerised in Fig. and Fig. . The larger inlet size of distorted region ệ 0 produces a larger change in mass flow rate. Meanwhile a smaller flow angle produces a higher pressure rise. This is easy to understand. Because ơ OR and we set Ơ V0 and OR as constants thus the vertical reference velocity V0 is a constant too. From the tandg Vo Uo a smaller 0 g will produce a larger U0 for a constant value of Vg thus a higher pressure rise. 98 Chapter 4 A Development of Novel Integral Method Fig. . The simulated compressor characteristics at higher inlet size of distorted region of _ I CM o o 00 5 00 15 00 25 0oO 0 0 0 z X UO M Fig. . The simulated compressor characteristics at smaller inlet size of distorted region of Concluding Remarks 99 Argument for Airfoil Characteristics As mentioned in Sect. we propose the airfoil lift and drag coefficients to be described as the functions of the angle of attack according to the wing section theory and experimental data C f a Cd f2 Ct Here the angles of attack for rotor and stator are described as following in the distorted region Figure ar tan 1 y as tan 1 y Y a The angles .
