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NACA-RM-L7K06
Two-dimensional wind-tunnel investigation at high Reynolds numbers of an NACA 65A006 airfoil with high-lift devices
Year: 1948
Abstract: INTRODUCTION
The use of thin airfoils on aircraft designed for this transonic and supersonic speed ranges has emphasized the need for the development of means to increase the naturally low maximum lift of these profiles in order to obtain satisfactory low-speed characteristics.
The results of an investigation to determine the low-speed characteristics of two symmetrical circular-arc airfoils, 6 and 10 percent thick, equipped with leading-edge and trailing-edge flaps, are presented in reference 1. Recent data indicate that thin NACA 6 series airfoils have lower drag in the transonic speed range than circular-arc airfoils. The present investigation was therefore made to furnish the lift, drag, and pitching-moment characteristics of an NACA 65A006 airfoil with the 0.20-chord plain trailing-edge flap and the 0.15 chord drooped-nose flap deflected individually and in appropriate combinations for comparison with the circular-arc airfoil sections. These tests were made in the Langley two-dimensional low turbulence tunnel, a variable-density wind tunnel which enables both the Reynolds number and Mach number appropriate to the landing condition for a typical airplane to be approximated simultaneously.
The use of thin airfoils on aircraft designed for this transonic and supersonic speed ranges has emphasized the need for the development of means to increase the naturally low maximum lift of these profiles in order to obtain satisfactory low-speed characteristics.
The results of an investigation to determine the low-speed characteristics of two symmetrical circular-arc airfoils, 6 and 10 percent thick, equipped with leading-edge and trailing-edge flaps, are presented in reference 1. Recent data indicate that thin NACA 6 series airfoils have lower drag in the transonic speed range than circular-arc airfoils. The present investigation was therefore made to furnish the lift, drag, and pitching-moment characteristics of an NACA 65A006 airfoil with the 0.20-chord plain trailing-edge flap and the 0.15 chord drooped-nose flap deflected individually and in appropriate combinations for comparison with the circular-arc airfoil sections. These tests were made in the Langley two-dimensional low turbulence tunnel, a variable-density wind tunnel which enables both the Reynolds number and Mach number appropriate to the landing condition for a typical airplane to be approximated simultaneously.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:59:41Z | |
| date available | 2017-09-04T16:59:41Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | XMMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/123117 | |
| description abstract | INTRODUCTION The use of thin airfoils on aircraft designed for this transonic and supersonic speed ranges has emphasized the need for the development of means to increase the naturally low maximum lift of these profiles in order to obtain satisfactory low-speed characteristics. The results of an investigation to determine the low-speed characteristics of two symmetrical circular-arc airfoils, 6 and 10 percent thick, equipped with leading-edge and trailing-edge flaps, are presented in reference 1. Recent data indicate that thin NACA 6 series airfoils have lower drag in the transonic speed range than circular-arc airfoils. The present investigation was therefore made to furnish the lift, drag, and pitching-moment characteristics of an NACA 65A006 airfoil with the 0.20-chord plain trailing-edge flap and the 0.15 chord drooped-nose flap deflected individually and in appropriate combinations for comparison with the circular-arc airfoil sections. These tests were made in the Langley two-dimensional low turbulence tunnel, a variable-density wind tunnel which enables both the Reynolds number and Mach number appropriate to the landing condition for a typical airplane to be approximated simultaneously. | |
| language | English | |
| title | NACA-RM-L7K06 | num |
| title | Two-dimensional wind-tunnel investigation at high Reynolds numbers of an NACA 65A006 airfoil with high-lift devices | en |
| type | standard | |
| page | 29 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext |