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NACA-RM-L53A29
Low-speed lateral control characteristics of an unswept wing with hexagonal airfoil sections and aspect ratio 4.0 at a Reynolds number of 6.2 x 10(exp 6)
Year: 1953
Abstract: INTRODUCTION
As part of the study of the low-speed characteristics of wings suitable for supersonic speeds a lateral-control investigation has been made of an unswept, modified double wedge wing of aspect ratio 4.0 in the Langley 19-foot pressure tunnel at high Reynolds numbers and low Mach members. Lateral-control investigations have been conducted previously for wings of similar plan form and airfoil section (NACA investigations Conducted at the Ames laboratory by Ben H. Johnson, Jr. and Fred A. Demele and by Noel K. Delany and Mora-Lee F. m e r and at the Langley Laboratory by James E. Fitzpatrick and Robert L. Woods ); however, there is a scarcity of data pertaining to aileron hinge moments. aileron normal forces and aileron balance-chamber pressures. This paper presents force measurements as well as aileron hinge moments, normal forces, and balance-chamber pressures. The tests included measurements of both a 0.79 semispan and an outboard 0.40 semispan aileron. The effects of leading-edge droop and part-span trailing-edge flaps on the outboard aileron effectiveness were also investigated. A l l tests were made with a cylindrical fuselage attached to the wing. No analysis is presented herein.
As part of the study of the low-speed characteristics of wings suitable for supersonic speeds a lateral-control investigation has been made of an unswept, modified double wedge wing of aspect ratio 4.0 in the Langley 19-foot pressure tunnel at high Reynolds numbers and low Mach members. Lateral-control investigations have been conducted previously for wings of similar plan form and airfoil section (NACA investigations Conducted at the Ames laboratory by Ben H. Johnson, Jr. and Fred A. Demele and by Noel K. Delany and Mora-Lee F. m e r and at the Langley Laboratory by James E. Fitzpatrick and Robert L. Woods ); however, there is a scarcity of data pertaining to aileron hinge moments. aileron normal forces and aileron balance-chamber pressures. This paper presents force measurements as well as aileron hinge moments, normal forces, and balance-chamber pressures. The tests included measurements of both a 0.79 semispan and an outboard 0.40 semispan aileron. The effects of leading-edge droop and part-span trailing-edge flaps on the outboard aileron effectiveness were also investigated. A l l tests were made with a cylindrical fuselage attached to the wing. No analysis is presented herein.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:26:15Z | |
| date available | 2017-09-04T15:26:15Z | |
| date copyright | 01/01/1953 | |
| date issued | 1953 | |
| identifier other | NNSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/26958 | |
| description abstract | INTRODUCTION As part of the study of the low-speed characteristics of wings suitable for supersonic speeds a lateral-control investigation has been made of an unswept, modified double wedge wing of aspect ratio 4.0 in the Langley 19-foot pressure tunnel at high Reynolds numbers and low Mach members. Lateral-control investigations have been conducted previously for wings of similar plan form and airfoil section (NACA investigations Conducted at the Ames laboratory by Ben H. Johnson, Jr. and Fred A. Demele and by Noel K. Delany and Mora-Lee F. m e r and at the Langley Laboratory by James E. Fitzpatrick and Robert L. Woods ); however, there is a scarcity of data pertaining to aileron hinge moments. aileron normal forces and aileron balance-chamber pressures. This paper presents force measurements as well as aileron hinge moments, normal forces, and balance-chamber pressures. The tests included measurements of both a 0.79 semispan and an outboard 0.40 semispan aileron. The effects of leading-edge droop and part-span trailing-edge flaps on the outboard aileron effectiveness were also investigated. A l l tests were made with a cylindrical fuselage attached to the wing. No analysis is presented herein. | |
| language | English | |
| title | NACA-RM-L53A29 | num |
| title | Low-speed lateral control characteristics of an unswept wing with hexagonal airfoil sections and aspect ratio 4.0 at a Reynolds number of 6.2 x 10(exp 6) | en |
| type | standard | |
| page | 26 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1953 | |
| contenttype | fulltext |