Numerical Investigation of the Aerodynamics of a Delta Wing in Ground Effect

2015 ◽  
Vol 52 (1) ◽  
pp. 329-340 ◽  
Author(s):  
Qiulin Qu ◽  
Zhe Lu ◽  
Hao Guo ◽  
Peiqing Liu ◽  
Ramesh K. Agarwal
Keyword(s):  
Numerical Investigation ◽  
Delta Wing ◽  
Ground Effect ◽  
Wing In Ground Effect

Ground effect on a cropped slender reverse delta wing with anhedral and Gurney flaplike side-edge strips

2018 ◽  
Vol 233 (7) ◽  
pp. 2433-2444 ◽  
Author(s):  
T Lee ◽  
D Huitema ◽  
P Leite
Keyword(s):  
Weight Reduction ◽  
Free Stream ◽  
Delta Wing ◽  
Ground Effect ◽  
Aerodynamic Coefficients ◽  
Side Edge ◽  
A Minor ◽  
Wing In Ground Effect

The ground effect on the aerodynamic coefficients of a cropped slender reverse delta wing equipped with anhedral and Gurney flaplike side-edge strips was investigated experimentally at Re = 3.82 × 105. In a free stream, the 30% cropping was found to cause a minor reduction in lift CL and drag CD coefficients but a promoted stall compared to the noncropped wing. The anhedral caused further CL decrease and CD increase. Meanwhile, the application of side-edge strips produced a significantly increased CL and CD with a minor change to the CL/ CD ratio as compared to the baseline wing. In ground effect, the cropped wing was, however, found to generate more lift compared to the noncropped wing as the ground was approached. The joint anhedral and SES produced a great increment in both CL and CD but a virtually unchanged CL/ CD ratio compared to their outside ground effect counterparts. The larger the side-edge strips’ height the larger the increase in CL. In short, the cropping led to a weight reduction while the addition of anhedral and SES produced a large lift augmentation of the Lippisch-type wing-in-ground effect craft.

Numerical Investigation on Aerodynamic Characteristics of a Compound Wing-in-Ground Effect

2012 ◽  
Vol 49 (5) ◽  
pp. 1297-1305 ◽  
Author(s):  
Saeed Jamei ◽  
Adi Maimun ◽  
Shuhaimi Mansor ◽  
Nor Azwadi ◽  
Agoes Priyanto
Keyword(s):  
Numerical Investigation ◽  
Ground Effect ◽  
Aerodynamic Characteristics ◽  
Wing In Ground Effect

Ground Effect on the Vortex Flow and Aerodynamics of a Slender Delta Wing

2018 ◽  
Vol 140 (7) ◽  
Author(s):  
T. Lee ◽  
L. S. Ko
Keyword(s):  
Vortex Breakdown ◽  
Delta Wing ◽  
Leading Edge ◽  
Ground Effect ◽  
Drag Forces ◽  
Wing Chord ◽  
Ground Distance ◽  
Lift And Drag ◽  
Wing Stall ◽  
Wing In Ground Effect

The ground effect on the aerodynamic loading and leading-edge vortex (LEV) flow generated by a slender delta wing was investigated experimentally. Both the lift and drag forces were found to increase with reducing ground distance (up to 50% of the wing chord). The lift increment was also found to be the greatest at low angles of attack α and decreased rapidly with increasing ground distance and α. The ground effect-caused earlier wing stall was also accompanied by a strengthened LEV with an increased rotational speed and size compared to the baseline wing. The smaller the ground distance, the stronger the LEV and the earlier vortex breakdown became. Meanwhile, the vortex trajectory was also found to be located further inboard and above the delta wing in ground effect compared to its baseline-wing counterpart. Finally, for wing-in-ground effect (WIG) craft with delta-wing planform the most effective in-ground-effect flight should be kept within 10% of the wing chord.

Ground effect on a slender reverse delta wing with anhedral

2018 ◽  
Vol 233 (4) ◽  
pp. 1516-1525
Author(s):  
T Lee ◽  
V Tremblay-Dionne ◽  
LS Ko
Keyword(s):  
Rotational Speed ◽  
Delta Wing ◽  
Ground Effect ◽  
Drag Coefficients ◽  
Drag Forces ◽  
Trailing Edges ◽  
Lift And Drag ◽  
Total Circulation ◽  
Wing In Ground Effect

The ground effect on the lift and drag forces and vortices generated by a slender reverse delta wing with different anhedrals was investigated experimentally. The study was inspired by the Lippisch-type RFB X-114 WIG (wing-in-ground effect) craft for which a reverse delta wing planform with anhedral was employed. The results show that, by positioning the trailing edges of the anhedraled reverse delta wing parallel to the ground, the lift and drag coefficients were found to increase persistently with increasing anhedral as the ground was approached (for ground distances within 40% chord). The observed lift augmentation was also accompanied by an ever-increasing rotational speed and total circulation of the vortices generated by the anhedraled wing. The vortices were also found to be displaced more outboard as the ground was approached, which further suggests their little relevance to the lift generation of the anhedraled reverse delta wing.

Numerical investigation of auto-pitch wing-in-ground effect oscillating foil propulsor

2019 ◽  
Vol 89 ◽  
pp. 71-84 ◽  
Author(s):  
Jiadong Wang ◽  
Pengfei Liu ◽  
Christopher Chin ◽  
Guanghua He
Keyword(s):  
Numerical Investigation ◽  
Ground Effect ◽  
Oscillating Foil ◽  
Wing In Ground Effect

scholarly journals Wing-in-ground-effect craft: A case study in aerodynamics

2018 ◽  
Vol 7 (4.13) ◽  
pp. 5 ◽  
Author(s):  
Surjatin Wiriadidjaja ◽  
Amzari Zhahir ◽  
Zahratu Hilall Mohamad ◽  
Shikin Razali ◽  
Ahmad Afifi Puaat ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Numerical Investigation ◽  
Public Transport ◽  
Ground Effect ◽  
Research Data ◽  
Natural Phenomenon ◽  
Longitudinal Stability ◽  
Wing In Ground Effect

A wing-in-ground-effect (WIGE) crafts can be deployed to fly by utilizing the ground effect, which is a natural phenomenon known to improve the efficiency of airplanes during take-off and landing approaches. In contrast, WIGE craft is not commercially viable for public transport mainly due to the difficulties in controlling its longitudinal stability. As an attempt to support the development of WIGE crafts, this paper presents a case study in aerodynamics based on certain published reports, specifically to reveal the available research data that are considered of interest and can be used as a lesson for further study and analysis. The wind tunnel procedure and testing, as well as numerical investigation of a WIGE craft, are applied and the results are then analyzed. The discussions are oriented in the perspectives of aerodynamics. Based on the tests and calculation, parameters concerning the ground effect as the WIGE crafts approaching the ground surfaces may be identified and hence their values can be determined. Thus, the static longitudinal stability may then be established and optimized for control of the WIGE craft.  

Smart Control Systems for Next-Generation Autonomous Wing-In-Ground Effect Vehicles

2010 ◽  
Vol 43 (15) ◽  
pp. 112-117 ◽  
Author(s):  
Alexander Nebylov ◽  
Sukrit Sharan ◽  
Farid Arifuddin
Keyword(s):  
Control Systems ◽  
Ground Effect ◽  
Next Generation ◽  
Smart Control ◽  
Wing In Ground Effect
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