Supersonic Retropropulsion Experimental Results from the NASA Ames 9- x 7-Foot Supersonic Wind Tunnel | Zendy

Scott A. Berry | Zendy; Matthew N. Rhode | Zendy; Karl T. Edquist | Zendy

AI Assistant Blog Pricing

Home ZAIA Blog

Open Access

Supersonic Retropropulsion Experimental Results from the NASA Ames 9- x 7-Foot Supersonic Wind Tunnel

Author(s) -

Scott A. Berry,

Matthew N. Rhode,

Karl T. Edquist

Publication year - 2012

Publication title -

42nd aiaa fluid dynamics conference and exhibit

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.2012-2704

Subject(s) - supersonic speed , wind tunnel , aerospace engineering , supersonic wind tunnel , aeronautics , marine engineering , engineering , geology

Supersonic retropropulsion was experimentally examined in the Ames Research Center 9x7-Foot Supersonic Wind Tunnel at Mach 1.8 and 2.4. The experimental model, previously designed for and tested in the Langley Research Center Unitary Plan Wind Tunnel at Mach 2.4, 3.5 and 4.6, was a 5-in diameter 70-deg sphere-cone forebody with a 9.55-in long cylindrical aftbody. The forebody was designed to accommodate up to four 4:1 area ratio nozzles, one on the model centerline and the other three on the half radius spaced 120-deg apart. Surface pressure and flow visualization were the primary measurements, including high-speed data to investigate the dynamics of the interactions between the bow and nozzle shocks. Three blowing configurations were tested with thrust coefficients up to 10 and angles of attack up to 20-deg. Preliminary results and observations from the test are provided.

The content you want is available to Zendy users.

Already have an account? Click here to sign in.

Having issues? You can contact us here

Accelerating Research