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NACA-RM-L52L05
Wind-tunnel investigation of stall control by suction through a porous leading edge on a 37 degrees sweptback wing of aspect ratio 6 at Reynolds numbers from 2.50 x 10(exp 6) to 8.10 x 10(exp 6)
Year: 1952
Abstract: INTRODUCTION
Considerable research in recent years has been carried on for the purpose of improving the low-speed longitudinal stability of sweptback wings. Most of this work has been concerned with delaying the tip stall by means of auxiliary devices such as leading-edge flaps, slats, or droop nose. (See, for instance, refs. 1 to 3. ) More recently, attention has been directed toward the possibility that stability at the stall might be obtained just as effectively by means of boundary-layer control.
Some data are available which demonstrate that longitudinal stability at the stall can be improved on sweptback wings by means of suction through leading-edge slots or porous area (refs.4 to 6 ). An appraisal of leading-edge suction as a stall-control devices on sweptback wings, however, can be made only if its effects can be directly compared with the effects of auxiliary deviance the same wing. In order to make this comparison and also to provide additional data showing the effects of leading-edge suction on sweptback wings, an investigation was maiden the Langley 19-foot pressure tunnel e on a 370 sweptback wing of aspect ratio 5 with suction through a porous leading edge. The effects of auxiliary devices on the same wing are s h m in reference 1.
The tests included few made with half-span split or double slotted flaps deflected and were made over a of Reynolds number from 2.50 x 106 to 8.10 x l06 and a range of Mach number 0.08 to 0.26.
Considerable research in recent years has been carried on for the purpose of improving the low-speed longitudinal stability of sweptback wings. Most of this work has been concerned with delaying the tip stall by means of auxiliary devices such as leading-edge flaps, slats, or droop nose. (See, for instance, refs. 1 to 3. ) More recently, attention has been directed toward the possibility that stability at the stall might be obtained just as effectively by means of boundary-layer control.
Some data are available which demonstrate that longitudinal stability at the stall can be improved on sweptback wings by means of suction through leading-edge slots or porous area (refs.4 to 6 ). An appraisal of leading-edge suction as a stall-control devices on sweptback wings, however, can be made only if its effects can be directly compared with the effects of auxiliary deviance the same wing. In order to make this comparison and also to provide additional data showing the effects of leading-edge suction on sweptback wings, an investigation was maiden the Langley 19-foot pressure tunnel e on a 370 sweptback wing of aspect ratio 5 with suction through a porous leading edge. The effects of auxiliary devices on the same wing are s h m in reference 1.
The tests included few made with half-span split or double slotted flaps deflected and were made over a of Reynolds number from 2.50 x 106 to 8.10 x l06 and a range of Mach number 0.08 to 0.26.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:48:06Z | |
| date available | 2017-09-04T18:48:06Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | KNSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;query=authoCA5893FD081D20686159DD6EFDEC014A/handle/yse/229289 | |
| description abstract | INTRODUCTION Considerable research in recent years has been carried on for the purpose of improving the low-speed longitudinal stability of sweptback wings. Most of this work has been concerned with delaying the tip stall by means of auxiliary devices such as leading-edge flaps, slats, or droop nose. (See, for instance, refs. 1 to 3. ) More recently, attention has been directed toward the possibility that stability at the stall might be obtained just as effectively by means of boundary-layer control. Some data are available which demonstrate that longitudinal stability at the stall can be improved on sweptback wings by means of suction through leading-edge slots or porous area (refs.4 to 6 ). An appraisal of leading-edge suction as a stall-control devices on sweptback wings, however, can be made only if its effects can be directly compared with the effects of auxiliary deviance the same wing. In order to make this comparison and also to provide additional data showing the effects of leading-edge suction on sweptback wings, an investigation was maiden the Langley 19-foot pressure tunnel e on a 370 sweptback wing of aspect ratio 5 with suction through a porous leading edge. The effects of auxiliary devices on the same wing are s h m in reference 1. The tests included few made with half-span split or double slotted flaps deflected and were made over a of Reynolds number from 2.50 x 106 to 8.10 x l06 and a range of Mach number 0.08 to 0.26. | |
| language | English | |
| title | NACA-RM-L52L05 | num |
| title | Wind-tunnel investigation of stall control by suction through a porous leading edge on a 37 degrees sweptback wing of aspect ratio 6 at Reynolds numbers from 2.50 x 10(exp 6) to 8.10 x 10(exp 6) | en |
| type | standard | |
| page | 68 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |