The aerodynamic coefficients were experimentally determined in a 30 x 30 sq cm supersonic wind tunnel for ranges of Mach number between 2.25 and 4.15 and angles of incidence -3 and 5 deg. Main attention was fixed on the gliding flight properties which are of importance for recovery and which were compared with those of a typical lifting reentry body (ERNO LB1). Results show that with reference to the maximum attainable range the lifting body possesses a gliding flight behavior better by an order of magnitude than that of the ballistic reentry body. Typical values of the lift-drag ratio are 0.1 for Neptun W1 and 1.5 for ERNO LB1. In contrast the static longitudinal stability of the ballistic flight vehicle is superior to that of the lifting body. The latter can only be maintained on a descending glide path in a trimmed flight state with the aid of aerodynamic control surfaces.
Aerodynamic Coefficients of the First Reentry-Stage of the Reusable Ballistic Rocket Neptun in Supersonic Flow Employing the Air Brakes as Control Surfaces
1976
270 pages
Report
Keine Angabe
Englisch
Spacecraft Trajectories & Flight Mechanics , Aerodynamic brakes , Aerodynamic coefficients , Lifting reentry vehicles , Wind tunnel tests , Control surfaces , Gliding , Lift drag ratio , Longitudinal stability , Spacecraft reentry , Supersonic flow , Supersonic wind tunnels , West Germany , Translations