Static force tests were conducted in the 40-in. supersonic tunnel of the von Karman Gas Dynamics Facility on a separable-nose crew escape capsule having cold flow simulation of the separation rocket jet plume. Data were obtained at Mach numbers from 1.5 to 6 at angles of attack from -30 to 30 deg and angles of sideslip from -15 to 15 deg. Reynolds number, based on a model length of 18.1 in., ranged from 1,360,000 to 12,300,000. Selected results are presented showing the effects of the rocket exhaust jet on the static stability and drag characteristics of the vehicle. (Author)
Force Tests on a Separable-Nose Crew Escape Capsule with Cold Flow Rocket Jet Simulation at Mach Numbers 1.5 Through 6
1966
34 pages
Report
No indication
English
Fluid Mechanics , Aircraft , Jettisonable cockpits , Jet fighters , Cold flow , Performance(Engineering) , Force(Mechanics) , Supersonic characteristics , Rocket engines , Exhaust gases , Angle of attack , Sideslip , Reynolds number , Stability , Drag , Supersonic flow , Wind tunnel models , Model tests , Trim tabs , Pitch(Motion) , Moments , Lift , Pressure , Flow separation , Yaw , Roll , High altitude , Low altitude , Experimental data , F-104 aircraft , Plumes(Radiation)