Drag reduction due to riblets on a NACA 0012 airfoil at higher angles of attack
IR@NAL: CSIR-National Aerospace Laboratories, Bangalore
View Archive Info| Field | Value | |
| Title |
Drag reduction due to riblets on a NACA 0012 airfoil at higher angles of attack
|
|
| Creator |
Subaschandar, N
Rajeev , Kumar Sundaram, S |
|
| Subject |
Aerodynamics
|
|
| Description |
Previous investigations of viscous drag reduction due to riblets on a NACA 0012 by Sundaram et a1 has been extended to higher angles of attack. Tests were made at a freestream velocity of 30 m/s and angle of attack (&) ranging from 8 to 12. Total airfoil-drag was determined from wake survey while pressure drag was obtained by integrating surface pressure distributions on the model. Skin friction drag was estimated from the difference between total and pressure drag. Results showed that both total and skin friction drag reduction which were found to be about 13% and 15% respectively at cC =6 , decreased rapidly with a further increase in, there was virtually no drag reduction at cC= 12:
|
|
| Publisher |
National Aerospace Laboratories
|
|
| Date |
1995-03
|
|
| Type |
Proj.Doc/Technical Report
NonPeerReviewed |
|
| Format |
application/pdf
|
|
| Identifier |
http://nal-ir.nal.res.in/12475/1/Drag_reduction.pdf
Subaschandar, N and Rajeev , Kumar and Sundaram, S (1995) Drag reduction due to riblets on a NACA 0012 airfoil at higher angles of attack. Technical Report. National Aerospace Laboratories, Bangalore. |
|
| Relation |
http://nal-ir.nal.res.in/12475/
|
|