Wind Tunnel Testing of a Blown Flap Wing

Agrawal, Devansh; Asad, Faisal; Berk, Blake M.; Long, Trevor; Lubin, Jackson; Courtin, Christopher; Drela, Mark; Hansman, R. John; Thomas, Jacqueline

doi:10.2514/6.2019-3170

Cited by 10 publications

(10 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The 2D section data used in this model is a fit to the wind tunnel test data, across the range of flap deflection, angles of attack, and c J tested. The details of this fitting are described in [18]; it shows reasonably agreement with the experimental data across the range of test data. Figure 5 shows a comparison between this wind tunnel data fit (solid red line) and a theoretical thin airfoil theory model (dashed blue line) for one representative high lift case with 40 flaps and c J = 3.…”

Section: D Section Datamentioning

confidence: 56%

See 1 more Smart Citation

Model Development for a Comparison of VTOL and STOL Electric Aircraft Using Geometric Programming

Courtin

Hansman

2019

AIAA Aviation 2019 Forum

Self Cite

View full text Add to dashboard Cite

There is widespread interest in the use of electric aircraft for short missions in and around urban areas. Most of the vehicle configurations proposed for these missions are electric Vertical Takeo and Landing (VTOL) configurations, due to perceived limitations on the available infrastructure. Several recent studies have proposed electric Short Takeo and Landing (STOL) aircraft with externally blown flaps as viable alternatives for urban operations. One of the claimed benefits of STOL aircraft is increased mission performance (in terms of range, payload, or speed) compared to an VTOL aircraft of the same weight. This study discusses the development of the models necessary to investigates this claim for a variety of possible missions, available infrastructure sizes, and levels of technology. Preliminary mission spaces where STOL or VTOL aircraft are the most weight-e cient choice are identified. The analysis is done using geometric programming, a convex optimization framework that enables rapid design re-optimization over a broad mission space. F Flap deflection Wake circulation µ Wheel friction coe cient ' Velocity potential Horseshoe vortex circulation

show abstract

Section: D Section Datamentioning

confidence: 56%

“…This study will take advantage of recent wind tunnel testing of a blown-wing section, detailed in [18]. That testing approximated the 2D section performance of a blown wing with a single-slotted trailing edge flap over a range of angles of attack, flap deflections, and blowing power settings.…”

Section: A Blown Wingmentioning

confidence: 99%

Model Development for a Comparison of VTOL and STOL Electric Aircraft Using Geometric Programming

Courtin

Hansman

2019

AIAA Aviation 2019 Forum

Self Cite

View full text Add to dashboard Cite

show abstract

“…For a blown wing, the lift coe cient C L varies strongly with angle of attack ↵, flap deflection F , and the jet momentum-excess coe cient C J . The latter represents the overall blowing intensity of all the propulsors, and can be defined by integrating the sectional c J across the span [4].…”

Section: Data Analysis Methodsmentioning

confidence: 99%

“…The empennage consisted of conventional horizontal and vertical stabilizers. The customized wing airfoil design was the same as tested in [4], with a 15% maximum thickness and a 38% chord flap. A cross section is shown in Figure 2.…”

Section: Vehicle Descriptionmentioning

confidence: 99%