Abstract
We report on an experimental study of a Clark-Y airfoil subjected to both flow injection and suction in the manner of the coflow-jet flow control method. The study was conducted at Reynolds numbers of 7.4 × 10 4 and 1.3 × 10 5 for three different jet momentum coefficients: C μ = 0.02, 0.04, and 0.16. Some numerical computations are used to assess the extent to which they are adequate for engineering analysis and design of the coflow-jet method. The results clearly demonstrate the lift augmentation capability, particularly at high incidence angles. The increase in lift and stall margin depends on the momentum coefficient, and for the range tested, the increase in the integral of the airfoil static pressure distribution varies from 40 to 100%. The results suggest that the coflow-jet airfoil is more effective when both injection and suction are used simultaneously, compared with the case in which they are individually used. A first-order analysis of the combined merits of injection and suction indicate that these processes are not strongly coupled to each other and thus may possibly be analyzed separately.
| Original language | English |
|---|---|
| Pages (from-to) | 291-300 |
| Number of pages | 10 |
| Journal | Journal of Aircraft |
| Volume | 46 |
| Issue number | 1 |
| DOIs | |
| State | Published - Jan 1 2009 |
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ASJC Scopus subject areas
- Aerospace Engineering
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Flow control of an airfoil via injection and suction. / Chng, T. L.; Rachman, A.; Tsai, H. M.; Zha, GeCheng.
In: Journal of Aircraft, Vol. 46, No. 1, 01.01.2009, p. 291-300.Research output: Contribution to journal › Article
}
TY - JOUR
T1 - Flow control of an airfoil via injection and suction
AU - Chng, T. L.
AU - Rachman, A.
AU - Tsai, H. M.
AU - Zha, GeCheng
PY - 2009/1/1
Y1 - 2009/1/1
N2 - We report on an experimental study of a Clark-Y airfoil subjected to both flow injection and suction in the manner of the coflow-jet flow control method. The study was conducted at Reynolds numbers of 7.4 × 10 4 and 1.3 × 10 5 for three different jet momentum coefficients: C μ = 0.02, 0.04, and 0.16. Some numerical computations are used to assess the extent to which they are adequate for engineering analysis and design of the coflow-jet method. The results clearly demonstrate the lift augmentation capability, particularly at high incidence angles. The increase in lift and stall margin depends on the momentum coefficient, and for the range tested, the increase in the integral of the airfoil static pressure distribution varies from 40 to 100%. The results suggest that the coflow-jet airfoil is more effective when both injection and suction are used simultaneously, compared with the case in which they are individually used. A first-order analysis of the combined merits of injection and suction indicate that these processes are not strongly coupled to each other and thus may possibly be analyzed separately.
AB - We report on an experimental study of a Clark-Y airfoil subjected to both flow injection and suction in the manner of the coflow-jet flow control method. The study was conducted at Reynolds numbers of 7.4 × 10 4 and 1.3 × 10 5 for three different jet momentum coefficients: C μ = 0.02, 0.04, and 0.16. Some numerical computations are used to assess the extent to which they are adequate for engineering analysis and design of the coflow-jet method. The results clearly demonstrate the lift augmentation capability, particularly at high incidence angles. The increase in lift and stall margin depends on the momentum coefficient, and for the range tested, the increase in the integral of the airfoil static pressure distribution varies from 40 to 100%. The results suggest that the coflow-jet airfoil is more effective when both injection and suction are used simultaneously, compared with the case in which they are individually used. A first-order analysis of the combined merits of injection and suction indicate that these processes are not strongly coupled to each other and thus may possibly be analyzed separately.
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UR - http://www.scopus.com/inward/citedby.url?scp=60049096591&partnerID=8YFLogxK
U2 - 10.2514/1.38394
DO - 10.2514/1.38394
M3 - Article
AN - SCOPUS:60049096591
VL - 46
SP - 291
EP - 300
JO - Journal of Aircraft
JF - Journal of Aircraft
SN - 0021-8669
IS - 1
ER -