Static-force tests were conducted on a separable-pod crew escape capsule in close proximity to the forward section of the airplane fuselage. The capsule escape rocket exhaust plume was simulated with high pressure air heated to a total temperature of approximately 100F. Data were obtained at Mach numbers from 2 through 5 at capsule angles of attack from -15 to 25 deg and angles of sideslip from 0 to 15 deg for various positions of the capsule relative to the fuselage section. All testing was conducted at a fuselage angle of attack and angle of sideslip of zero. Results are presented showing the effects of the fuselage section on the aerodynamic characteristics of the capsule, with and without simulation of the escape rocket exhaust plume. These results indicate that the primary interference effects for the jet-off data are caused by severe flow interactions occurring when the capsule, with its strong bow shock, moves across the fuselage cavity. For the jet-on data the primary interference effects are caused by the jet exhausting into the fuselage cavity, which acts as a flow deflector turning the jet flow back onto the capsule. (Author)
Force Tests on a Separable-Pod Crew Escape Capsule in Proximity to the Parent Fuselage at Mach Numbers 2 Through 5
1970
127 pages
Report
Keine Angabe
Englisch
Aircraft , Human Factors Engineering , Emergency Services & Planning , Fluid Mechanics , Supersonic aircraft , Aerospace systems , Jettisonable cockpits , Aerodynamic characteristics , Wind tunnel models , Aerodynamic loading , Rarefied gas dynamics , Jets , Yaw , Pitch(Motion) , Roll , Moments , Interactions , Ejectionable capsules , Plumes