%0 Journal Article
%T Numerical Study on Low-Reynolds Compressible Flows around Mars Helicopter Rotor Blade Airfoil
%A Takuma Yamaguchi
%A Masayuki Anyoji
%J Journal of Flow Control, Measurement & Visualization
%P 30-48
%@ 2329-3330
%D 2023
%I Scientific Research Publishing
%R 10.4236/jfcmv.2023.112003
%X High-speed rotor rotation under the low-density condition creates a special low-Reynolds compressible flow around the rotor blade airfoil where the compressibility effect on the laminar separated shear layer occurs. However, the compressibility effect and shock wave generation associated with the increase in the Mach number (<i>M</i>) and the trend change due to their interference have not been clarified. The purpose is to clear the compressibility effect and its impact of shock wave generation on the flow field and aerodynamics. Therefore, we perform a two-dimensional unsteady calculation by Computational fluid dynamics (CFD) analysis using the CLF5605 airfoil used in the Mars helicopter Ingenuity, which succeeded in its first flight on Mars. The calculation conditions are set to the Reynolds number (<i>Re</i>) at 75% rotor span in hovering (<i>Re</i> = 15,400), and the Mach number was varied from incompressible (<i>M</i> = 0.2) to transonic (<i>M</i> = 1.2). The compressible fluid dynamics solver FaSTAR developed by the Japan aerospace exploration agency (JAXA) is used, and calculations are performed under multiple conditions in which the Mach number and angle of attack (<i>¦Á</i>) are swept. T<a name=\"_Hlk124197144\"></a><span style=\"white-space:normal;\"><span style=\"font-family:;\" \"=\"\">he results show that a flow field is similar to that in the Earth¡¯s atmosphere above <i>M</i> = 1.0, such as bow shock at the leading edge, whereas multiple <i>¦Ë</i>-type shock waves are observed over the separated shear layer above <i>¦Á</i> = 3<span style=\"white-space:nowrap;\">¡ã</span> at <i>M</i> = 0.80</span></span><span style=\"white-space:normal;\"><span style=\"font-family:;\" \"=\"\">. However, no significant difference is found in the <i>C<sub>p</sub></i> distribution around the airfoil between <i>M</i> = 0.6 and <i>M</i> = 0.8. <a name=\"_Hlk123921919\"></a>From the results, it is found that multiple <i>¦Ë</i>-type shock waves have no significant effect on the airfoil surface pressure distribution, the separated shear layer effect is dominant in the surface pressure change and aerodynamic characteristics.</span></span>
%K CFD
%K CLF5605 Rotor Blade Airfoil
%K Compressibility Effect
%K Low-Reynolds Number
%K Mars Helicopter
%K Separation Bubble
%K Shock Wave
%U http://www.scirp.org/journal/PaperInformation.aspx?PaperID=124626