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NACA-RM-L8K19
Wind-tunnel investigation at low speeds of various plug-aileron and lift-flap configurations on a 42 degrees sweptback semispan wing
Year: 1949
Abstract: INTRODUCTION
The spoiler type of control device has been proposed in reference 1 as a means of lateral control for sweptback wings. All of the spoiler configurations reported in reference however, had some of the objection-able characteristics normally associated with spoilers on unswept wings; namely, a large reduction in rolling-moment coefficient at high angles of attack and low or reversed effectiveness at small spoiler projections for all angles of attack. Unpublished data showing the favorable rolling-moment characteristics in the transonic speed range obtained by one of that further work toward improving the low-speed characteristics of spoilers on swept wings would be desirable. Reference 2 and 3 reported that the plug aileron (formed by the installation of a slot through the wing behind the spoiler) on unswept wings eliminated the objectionable rolling-moment characteristics exhibited by plain spoilers. References 2 and 3 further showed that the installation of a full-span slotted flap, in addition to giving high maximum lift coefficients for landing, greatly improved the foiling-moment effectiveness of the plug aileron.
Reported herein are the results of a high-lift and lateral-control investigation performed on a 42 sweptback semi span-wing model in the Langley 300 MPH 7-by 10-foot tunnel. The high-lift characteristics of a full-span slotted flap were determined on this model for a range of flap deflections and positions, and an attempt was made to improve the maximum lift characteristics of the full-span slotted flap by the installation of flap-slot flow-control vanes. The high-lift characteristics of a half-span slotted flap at one deflection and position and of a half-span zap flap were also determined A comparison of the calculated trimmed gliding characteristics of the 42 sweptback wing under an assumed set of airplane conditions and equipped with several types and spans of lift flaps was made. Included in the lateral-control part of the investigation were the determination of the lateral control characteristics of a basic plug aileron and several revisions thereof. In addition, the characteristics of a 49 percent-span by 20 percent-chord plain aileron were determined for comparison with the plug-aileron results. Also determined were the lateral control characteristics of the most satisfactory plug-aileron configuration with the full-span slotted flap deflected to its optimum deflection and position and of the partial-span aileron with the partial-span slotted flap deflected.
The spoiler type of control device has been proposed in reference 1 as a means of lateral control for sweptback wings. All of the spoiler configurations reported in reference however, had some of the objection-able characteristics normally associated with spoilers on unswept wings; namely, a large reduction in rolling-moment coefficient at high angles of attack and low or reversed effectiveness at small spoiler projections for all angles of attack. Unpublished data showing the favorable rolling-moment characteristics in the transonic speed range obtained by one of that further work toward improving the low-speed characteristics of spoilers on swept wings would be desirable. Reference 2 and 3 reported that the plug aileron (formed by the installation of a slot through the wing behind the spoiler) on unswept wings eliminated the objectionable rolling-moment characteristics exhibited by plain spoilers. References 2 and 3 further showed that the installation of a full-span slotted flap, in addition to giving high maximum lift coefficients for landing, greatly improved the foiling-moment effectiveness of the plug aileron.
Reported herein are the results of a high-lift and lateral-control investigation performed on a 42 sweptback semi span-wing model in the Langley 300 MPH 7-by 10-foot tunnel. The high-lift characteristics of a full-span slotted flap were determined on this model for a range of flap deflections and positions, and an attempt was made to improve the maximum lift characteristics of the full-span slotted flap by the installation of flap-slot flow-control vanes. The high-lift characteristics of a half-span slotted flap at one deflection and position and of a half-span zap flap were also determined A comparison of the calculated trimmed gliding characteristics of the 42 sweptback wing under an assumed set of airplane conditions and equipped with several types and spans of lift flaps was made. Included in the lateral-control part of the investigation were the determination of the lateral control characteristics of a basic plug aileron and several revisions thereof. In addition, the characteristics of a 49 percent-span by 20 percent-chord plain aileron were determined for comparison with the plug-aileron results. Also determined were the lateral control characteristics of the most satisfactory plug-aileron configuration with the full-span slotted flap deflected to its optimum deflection and position and of the partial-span aileron with the partial-span slotted flap deflected.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:50:08Z | |
| date available | 2017-09-04T18:50:08Z | |
| date copyright | 01/01/1949 | |
| date issued | 1949 | |
| identifier other | KTSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsessionid=3826AF679D40527318548F1EFDEC014A/handle/yse/231479 | |
| description abstract | INTRODUCTION The spoiler type of control device has been proposed in reference 1 as a means of lateral control for sweptback wings. All of the spoiler configurations reported in reference however, had some of the objection-able characteristics normally associated with spoilers on unswept wings; namely, a large reduction in rolling-moment coefficient at high angles of attack and low or reversed effectiveness at small spoiler projections for all angles of attack. Unpublished data showing the favorable rolling-moment characteristics in the transonic speed range obtained by one of that further work toward improving the low-speed characteristics of spoilers on swept wings would be desirable. Reference 2 and 3 reported that the plug aileron (formed by the installation of a slot through the wing behind the spoiler) on unswept wings eliminated the objectionable rolling-moment characteristics exhibited by plain spoilers. References 2 and 3 further showed that the installation of a full-span slotted flap, in addition to giving high maximum lift coefficients for landing, greatly improved the foiling-moment effectiveness of the plug aileron. Reported herein are the results of a high-lift and lateral-control investigation performed on a 42 sweptback semi span-wing model in the Langley 300 MPH 7-by 10-foot tunnel. The high-lift characteristics of a full-span slotted flap were determined on this model for a range of flap deflections and positions, and an attempt was made to improve the maximum lift characteristics of the full-span slotted flap by the installation of flap-slot flow-control vanes. The high-lift characteristics of a half-span slotted flap at one deflection and position and of a half-span zap flap were also determined A comparison of the calculated trimmed gliding characteristics of the 42 sweptback wing under an assumed set of airplane conditions and equipped with several types and spans of lift flaps was made. Included in the lateral-control part of the investigation were the determination of the lateral control characteristics of a basic plug aileron and several revisions thereof. In addition, the characteristics of a 49 percent-span by 20 percent-chord plain aileron were determined for comparison with the plug-aileron results. Also determined were the lateral control characteristics of the most satisfactory plug-aileron configuration with the full-span slotted flap deflected to its optimum deflection and position and of the partial-span aileron with the partial-span slotted flap deflected. | |
| language | English | |
| title | NACA-RM-L8K19 | num |
| title | Wind-tunnel investigation at low speeds of various plug-aileron and lift-flap configurations on a 42 degrees sweptback semispan wing | en |
| type | standard | |
| page | 47 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext |