Numerical and Experimental Analysis of a Generic Fan-in-Wing Configuration

Thouault, N.; Breitsamter, Christian; Adams, Nikolaus A.

doi:10.2514/1.39750

Cited by 20 publications

(17 citation statements)

References 14 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The settings for the transition study were used. With 30 m/s freestream velocity, corresponding to a Reynolds number Re = 1.5 × 10 6 , and fan rotational speed of 21,000 rpm, the CFD predictions of C L and C m showed a good agreement with the experimental data (Figure 5b,c), which came from Thouault [3], while C D was a little under-predicted. …”

Section: Numerical Model Validationsupporting

confidence: 69%

“…The validation of transition mode was performed using a three-dimensional fan-in-wing configuration with a fan rotating in the plane of a wing [3]. One single circular fan was submerged at the rear part of the wing as in the case of the annular lift fan (Figure 5a).…”

Section: Numerical Model Validationmentioning

confidence: 99%

“…The concept of the annular lift fan originated from lift fan, including the fan-in-wing and fan-in-fuselage configurations, which were first implemented in the jet powered experimental aircraft Ryan GE XV-5 in the 1960s [3,4]. The fan-in-fuselage was recently incorporated in the F-35B II Lightning Joint Strike Fighter [5].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Numerical Study of Transition of an Annular Lift Fan Aircraft

Jiang

Zhang

2016

Aerospace

View full text Add to dashboard Cite

The present study aimed at studying the transition of annular lift fan aircraft through computational fluid dynamics (CFD) simulations. The oscillations of lift and drag, the optimization for the figure of merit, and the characteristics of drag, yawing, rolling and pitching moments in transition are studied. The results show that a two-stage upper and lower fan lift system can generate oscillations of lift and drag in transition, while a single-stage inner and outer fan lift system can eliminate the oscillations. The characteristics of momentum drag of the single-stage fans in transition are similar to that of the two-stage fans, but with the peak of drag lowered from 0.63 to 0.4 of the aircraft weight. The strategy to start transition from a negative angle of attack −21 • further reduces the peak of drag to 0.29 of the weight. The strategy also reduces the peak of pitching torque, which needs upward extra thrusts of 0.39 of the weight to eliminate. The peak of rolling moment in transition needs differential upward thrusts of 0.04 of the weight to eliminate. The requirements for extra thrusts in transition lead to a total thrust-weight ratio of 0.7, which makes the aircraft more efficient for high speed cruise flight (higher than 0.7 Ma).

show abstract

Section: Numerical Model Validationsupporting

confidence: 69%

Section: Numerical Model Validationmentioning

confidence: 99%

See 1 more Smart Citation

Numerical Study of Transition of an Annular Lift Fan Aircraft

Jiang

Zhang

2016

Aerospace

View full text Add to dashboard Cite

show abstract

“…The validation of transition mode was performed using a three-dimensional fan-in-wing configuration with a fan rotating in the plane of a wing [4,6]. The CFD predictions of C L and C m showed a good agreement with the experimental data, while C D was a little under-predicted [4].…”

Section: Numerical Model Validationmentioning

confidence: 91%

“…The lift fan was first implemented in the jet powered experimental aircraft Ryan GE XV-5 in 1960s [6]. Many experimental investigations have been conducted [7][8][9].…”

Section: Geometrymentioning

confidence: 99%

CFD Study of a New Annular Lift Fan Configuration with High Lift Efficiency

Jiang

Zhang

2017

Aerospace

View full text Add to dashboard Cite

Abstract:A new annular lift fan configuration that has very high lift efficiency is explored by using a numerical scheme. The inlet lip radius and diffuser angle are maximized by semicircle duct walls and the location of the lift fan is moved from the throat to the diffuser area to maximize the diffusion effect of the ducted fan. The improved lift fan achieves the figure of merit of 0.772 and the power loading of 9.03 lbs/hp without ground effect, very close to the theoretical limit. Under the ground effect, the figure of merit reaches 0.822 with the power loading of 9.62 lbs/hp. The improved lift efficiency deteriorates the transition characteristics with higher momentum drag and pitching moment. However, with the aid of jet thrusts directly providing part of the lift during transition, the peak of momentum drag and pitching moment can be lowered. A total thrust to weight ratio of 0.7 is enough for all of the requirements in transition and in hover and for the maximum speed of 0.75 Mach in cruise flight.

show abstract