A coUai>oraUon bet..een Coliromia Polytechnic Corporation wlt~ Georgia Tech Re.eorch In.tltu'" (GTRij ond DHC Engineering ..orked on , NASA NRA to de••lop prodlotlve .apabllJties ror tbe design ond perform,noe of Crul,e Emdent, Sbort Tok...Off ond Landing (CESTOL) 'Ub'Dnle ol..,r.ft, In addillon, 0 lorge .eal. wind tunDel effort to ,aUdat. tb••e p..didi.e o.pobiJlti•• ror thl. NRA for o.rodyn.mic ond ooou.lle p.rform.nc. during to!leoff .nd landing ha, boon und.rtak.D. Tb. mod.l, Ad ••no.d Model fnr E.tr.me Lift .nd Impro.ed Aeroacou,llo. (AMELIA), wa. designed •• 0 100 p,,,enger, N+2 generotlon, reglonal, erul.. .mol.nt ,bort tok...ff 'nd land (CllSTOLj alrUn", with hybrid bl.nded wing-body wltb drculallon contrnl nnd upper ,urf... blowing. Tbe model design wa. roeu.ed on ru.Hoylng' .nd nols. gool••et ODt by the NASA N+2 deflnUlon. The AMELIA hO' a 10 ft wing .p.n. P.t.....nL.b. w.. oba.. n to build AMELIA. Th. Nollon.1 I'UII•Soal. AerodynamIc Complex (NFAC) 40 ft by 80 ft wind tunnel wa. eho,.n to p.rform the l.rg....""I. wind runnelte.t in tb. 'Dmmer or 2011.
Results from Cal Poly's recent wind tunnel test in the 40-by 80-foot test section at the National Full-Scale Aerodynamics Complex (NFAC) at NASA Ames Research Center are presented. AMELIA, the Advanced Model for Extreme Lift and Improved Aeroacoustics, is the first full-span cruise efficient short takeoff and landing (CESTOL) model incorporating leading-and trailing-edge blowing wing circulation control and over-the-wing mounted turbine propulsion simulators (TPS) to date. Testing of the 10 foot span model proved successful and was the result of a 5-year NASA Fundamental Aeronautics Program Research Announcement. All of the results associated with Cal Poly's effort will be available in an open-source validation database with the goal of advancing the state-of-the-art in prediction capabilities for modeling aircraft with next generation technologies, focusing on NASA's N+2 generation goals. The model's modular design allowed for testing of 4 major configurations. Results from all configurations are presented. Test data shows drastic improvements in performance are obtained when incorporating leading edge blowing. Wing stall can be delayed to more than 25° angle of attack at lift coefficients exceeding six. Without the introduction of leading edge blowing to increase boundary layer momentum and maintain flow attachment around the leading edge, STOL performance suffers. Similar runs for trailing edge-only blowing show a reduction in maximum lift coefficient to three with stall occurring at zero angle of attack. Testing at multiple engine pylon heights allowed for the highly coupled propulsion and flow control system to be characterized.
A collaboration between California Polytechnic Corporation with GeorgiaTech Research Institute (GTRI) and DHC Engineering worked on a NASA NRA to develop predictive capabilities for the design and performance of Cruise Efficient, Short Take-Off and Landing (CESTOL) subsonic aircraft. The work presented in this paper gives details of a large scale wind tunnel effort to validate predictive capabilities for this NRA for aerodynamic and acoustic performance during takeoff and landing. The model, Advanced Model for Extreme Lift and Improved Aeroacoustics (AMELIA), was designed as a 100 passenger, N+2 generation, regional, cruise efficient short takeoff and land (CESTOL) airliner with hybrid blended wing-body with circulation control. AMELIA is a 1/11 scale with a corresponding 10 ft wing span. The National Full-Scale Aerodynamic Complex (NFAC) 40 ft by 80 ft wind tunnel was chosen to perform the large-scale wind tunnel test. The NFAC was chosen because both aerodynamic and acoustic measurements will be obtained simultaneously, the tunnel is large enough that the 2 downwash created by the powered lift did not impinge on the tunnel walls, and the schedule and cost fit into Cal Poly's time frame and budget. Several experimental measurement techniques were used to obtain the necessary data to validate predictive codes being developed as apart of this effort: along with the traditional forces and moments measurements, stationary microphones were used to obtain far-field acoustic measurements including a 48 element phased array, the Fringe-Image Skin Friction (FISF) technique was used to measure the global skin friction on the wing, surface mounted steady and unsteady pressure transducers were used to obtain local pressure distributions over the model, and oil and smoke flow visualization techniques were employed to understand the effects of the powered lift system in AMELIA. The paper gives a brief summary of AMELIA's performance for variable tunnel speed, momentum mass flow, engine simulator height, and angle of attack.
A collaboration between California Polytechnic Corporation with Georgia Tech Research Institute (GTRI) and DHC Engineering worked on a NASA NRA to develop predictive capabilities for the design and performance of Cruise Efficient, Short TakeOff and Landing (CESTOL) subsonic aircraft. The focus of this work presented in this paper gives details of a large scale wind tunnel effort to validate predictive capabilities for this NRA for aerodynamic and acoustic performance during takeoff and landing. The model, Advanced Model for Extreme Lift and Improved Aeroacoustics (AMELIA), was designed as a 100 passenger, N+2 generation, regional, cruise efficient short takeoff and land (CESTOL) airliner with hybrid blended wing-body with circulation control. AMELIA is a 1/11 scale with a corresponding 10 ft wing span. The National Full-Scale Aerodynamic Complex (NFAC) 40 ft by 80 ft wind tunnel was chosen to perform the large-scale wind tunnel test in the scheduled to start summer of 2011. The NFAC was chosen because both aerodynamic and acoustic measurements will be obtained simultaneously, the tunnel is large enough that the downwash created by the powered lift will not impinge on the tunnel walls, and the schedule and cost fit into Cal Poly's time frame and budget. Several experimental measurement techniques will be used to obtain the necessary data to validate predictive codes being developed as apart of this effort: stationary microphones will be used to obtain far-field acoustic measurements including a 48 element phased array, the Fringe-Image Skin Friction (FISF) technique will be used to measure the global skin friction on the wing, and the a micro flow measurement device will measure the velocity profiles in the in the boundary and shear layers is still in development and presented in this paper.
This paper details the extensive effort required to achieve uniform flow from the AMELIA wind tunnel model's circulation control wings. Performed in September of 2011 in the Fluid Mechanics Lab at NASA Ames Research Center, the calibration required a 500hp instrument-quality air compressor capable of delivering 250 CFM at pressures greater than 70 psi. It was found that the geometery within AMELIA's circulation control supply plenums produced highly vortical flow, resulting in poor circulation control performance as measured by traversing external and stationary internal total pressure probes, as well as surface oil flow. Adjustments were made within AMELIA to the supply conditions of each plenum including internal butterfly valve position, model inlet pressure, and total volume flow rate delivered to the model. Each plenum was further modified with a treatment of metal foam and various other materials including perforated plates, metal barriers, and Rigimesh material. The combination of metal foam and densly woven Rigimesh resulted in uniform spanwise flow at acceptable plenum pressures.
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