STOL Performance of Cal Poly's AMELIA

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.

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“…For a more in-depth evaluation, see Ref. 4. Data acquired during an alpha sweep were generally obtained over a range from -5° to +25°.…”

Section: Results Overviewmentioning

confidence: 99%

“…Results and discussion of the circulation control performance, over the wing mounted engines, and the combined performance is also briefly discussed, a more in-depth discussion of the wind tunnel test results can be found in Ref. 4.…”

Section: Introductionmentioning

confidence: 99%

Cal Poly's AMELIA 10 Foot Span Hybrid Wing-Body Low Noise CESTOL Aircraft Wing Tunnel Test and Experimental Results Overview

Jameson

Marshall

Ehrmann

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…The free shear layer developing from the sharp lower TE collide the slat TE pressure surface, affecting drag and noise during take-off and landing c tions [19]. Research has shown that the combination of LE blowing and internal-b flaps can effectively increase the stall angle of attack and maximum lift coefficien reduce the noise of the aircraft [15,20].…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on the Combined Blowing Control of a Hybrid Wing Body Aircraft

et al. 2023

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Combined blowing was performed on a Hybrid Wing Body (HWB) aircraft through wind tunnel testing at a Reynolds number of 1.75 × 106. The full cycle of separation and reattachment under the control of combined blowing was implemented using Computational Fluid Dynamics (CFD), and the mechanism of combined blowing inhibiting separation was analyzed. The aerodynamic characteristics of the baseline and the independent effects of the blown deflected trailing edge (TE), blown leading edge (LE), and combined blowing on the TE and LE were investigated. The results clearly show that combined blowing can inhibit the development of cross-flow, reduce the accumulation of a boundary layer at the tip, and inhibit the flow separation effect. The effect of using seamless simple flaps alone to increase the lift is limited; blowing control is required to enhance the lift further. Applying the blown deflected TE can improve the lift linear segment, so that 30° flap achieves the lift gain of 40° flap without control, while the drag coefficient is approximately 0.02 smaller, but the stall gradually advances. Using the blown LE can significantly increase the stall angle from 12° to 18°. However, the lift linear segment remains unaffected. In particular, combined blowing can achieve the control effect of improving the lift linear segment, delaying stall, and decreasing drag. Moreover, the maximum lift coefficient is approximately 0.19, and the lift-to-drag ratio increment in the control state with a 30° flap deflection angle is above 2.2 in the angle of attack range of 4° to 12° compared to the uncontrolled state with a 40° flap deflection angle.

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“…For more information on the aircraft design, wind tunnel model, wind tunnel test, results, and project as a whole see ref. [1][2][3][4].…”

Section: Introductionmentioning

confidence: 99%

Flow Uniformity Calibration of AMELIA's Circulation Control Wings

Paciano

Lichtwardt

Marshall

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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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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STOL Performance of Cal Poly's AMELIA

Cited by 5 publications

References 15 publications

Cal Poly's AMELIA 10 Foot Span Hybrid Wing-Body Low Noise CESTOL Aircraft Wing Tunnel Test and Experimental Results Overview

Cal Poly's AMELIA 10 Foot Span Hybrid Wing-Body Low Noise CESTOL Aircraft Wing Tunnel Test and Experimental Results Overview

Experimental Investigation on the Combined Blowing Control of a Hybrid Wing Body Aircraft

Flow Uniformity Calibration of AMELIA's Circulation Control Wings

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