Numerical investigation of aerodynamic characteristics of naca 23112 using passive flow control technique – gurney flaps

Figures & data

Figure 1. Aerodynamic characteristics with a 0.01c-high flap located at the trailing edge on the upper and lower surfaces (Maughmer & Bramesfeld, 2008).

Figure 2. Airfoil design with parameters to be varied.

Table 2. Geometric and operational parameters

Parameter	Value
Airfoil	NACA 23,112
Chord length (c)	1 m
Height of GF	0.01c, 0.02c, 0.03c
Thickness of GF	2 mm
Position of GF (from LE)	0.95c, 0.97c, c
Velocity	32.99 m/s
Re	2 × 10^6
Air Density	1.184 kg/m^3
Dynamic Viscosity	1.86 × 10^−5 N s/m^2

Figure 3. Extent of domain and mesh, showing the boundary conditions used for the study.

(Dimensions are in metres, numbers inside circles represent zones) 27

Table 1. Mesh sensitivity analysis

Name of Mesh	No. of elements	Cl	Error
M1	1.65 × 10^6	1.0125364	9.58
M2	2.12 × 10^6	1.1419066	1.9 %
M3	2.58 × 10^6	1.1396654	1.7 %

Figure 4. Validation plot of C_l with experimental data (Jacobs & Pinkerton, 1936).

Figure 5. Validation plot of C_d with experimental data (Jacobs & Pinkerton, 1936).

Figure 6. Comparison of C_l values obtained from CFD and experimental data (Maughmer & Bramesfeld, 2008).

Figure 7. Flowchart of steps carried out during the study.

Figure 8. (A) C_l vs AoA 1-YY, (B) C_l vs AoA 2-YY, (C) C_l vs AoA 3-YY, (C) Comparison of C_l among best configurations with 1, 2 and 3% c flaps.

Figure 9. (A) C_d vs AoA 1-YY, (B) C_d vs AoA 2-YY, (C) C_d vs AoA 3-YY, (C) Comparison of C_d among best configurations with 1, 2 and 3% c flaps 33.

Figure 10. Comparison of drag coefficients with varying flap height at AoA = 7.5° 35.

Figure 11. (A) C_l/C_d vs AoA 1-YY, (B) C_l/C_d vs AoA 2-YY, (C) C_l/C_d vs AoA 3-YY, (C) Comparison of C_l/C_d among best configurations with 1, 2 and 3% c flaps.

Table 3. Maximum values of C_l/C_d for each configuration

Variant name	Max Increment in Cl/Cd
1–95	33.418820
1–97	33.170700
1–100	37.939919
2–95	21.642771
2–97	23.355518
2–100	23.154778
3–95	32.600407
3–97	34.065601
3–100	33.853162

Figure 12. Pressure contours for (A) Plain wing at 10° AoA (B) TE of Plain wing at 10° AoA (C) 1–95 at 10° AoA (D) TE of 1–95 at 10° AoA (E) 2–95 at 10° AoA (F) TE of 2–95 at 10° AoAA.

Figure 13. Velocity contours for (A) Plain wing at 10° AoA (B) TE of Plain wing at 10° AoA (C) 1–95 at 10° AoA (D) TE of 1–95 at 10° AoA (E) 2–95 at 10° AoA (F) TE of 2–95 at 10° AoAC.

Maughmer, M. D., & Bramesfeld, G. (2008). Experimental investigation of Gurney flaps. Journal of Aircraft, 45(6), 2062–2067. https://doi.org/10.2514/1.37050

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Jacobs, E. N. and Pinkerton, R. M., (1936). “NACA-Report 537.”

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