An unmanned winged vehicle for space transportation called the H-II Orbiting Plane (HOPE) was studied by the National Space Development Agency of Japan (NASDA). The gross weight is planned about 9.0 tons at launch with the payload of about 1.2 tons. The current baseline configuration of the HOPE has a double delta wing with tip fins. The double delta type wing planform is expected to have smaller longitudinal trim change over all the flight regions. Tip fins are adopted in order to gain easier access to Space Station or other platforms. Hypersonic computational fluid dynamics (CFD) analyses were performed for the 62A, 62B, and 62C HOPE configurations in order to investigate lateral and directional aerodynamic characteristics. This work has been done as the joint research of National Aerospace Laboratory (NAL) and NASDA. Numerical computations were carried out at M(infinity) = 7.0 and Reynolds number of 2.5 x 10(exp 6) at angles of attack 0, 20 and 40 degrees with yaw angle of 5 deg. Numerical results were compared with experimental data obtained from the hypersonic wind tunnel (HWT) at NAL.
Numerical Simulation of Hypersonic Flow around H-2 Orbiting Plane
1989
7 pages
Report
No indication
English
Spacecraft Trajectories & Flight Mechanics , Aerodynamics , Fluid Mechanics , Aerodynamic characteristics , Aerospace planes , Computational fluid dynamics , Delta wings , Fins , Hypersonic flow , Hypersonics , Computerized simulation , Angle of attack , Angles (Geometry) , Hypersonic wind tunnels , Japan , Launching , Payloads , Reynolds number , Space stations , Space transportation , Stabilizers (Fluid dynamics) , Tail assemblies , Yaw , Foreign technology