Accession Number : AD0286316

Title :   SUPPLEMENTARY LIFT FOR AIR CUSHIONED VEHICLES. VOLUME 2. DATA ANALYSIS

Corporate Author : GRUMMAN AIRCRAFT ENGINEERING CORP BETHPAGE NY

Personal Author(s) : KIRSCHBAUM, N ; HELGESEN, J

PDF Url : AD0286316

Report Date : Jun 1962

Pagination or Media Count : 179

Abstract : The wind tunnel study of supplemental lift for air cushioned vehicles utilized a three-dimensional, half-span reflection-plane, airfoilshaped GEM model and covered speeds from 0 to 100 mph. The effects of various leading and trailing edge jet configurations on the performance of the model at zero degree angle of attack were evaluated. The data are presented in parametric form as a function of air mass flow coefficient. The results of this study indicated that the propulsive requirements for the lift system decreased with increasing speed or, for constant power the operating height can be increased. The stability characteristics of the cruise configurations at cruise speed (100 mph were also evaluated). The results of these tests indicated that all cruise configurations tested could be made longitudinally stable b locating the moment reference center (cg) at the 37% air cushion base chord. For the Jet lap configurations, the required nose down trim loads increased with increasing mass flow. With the Tip Jet Only Configuration, there was an adverse rolling moment with roll angle. This was the only configuration tested in roll.

Descriptors :   *FLYING PLATFORMS, AERODYNAMIC CHARACTERISTICS, AERODYNAMIC CONFIGURATIONS, AIRFOILS, AIRSPEED, GROUND EFFECT MACHINES, LIFT, MODEL TESTS, ROLL, STABILITY, WIND TUNNEL MODELS

Subject Categories : Research and Experimental Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE