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NACA-RM-L7I30
Yaw characteristics and sidewash angles of a 42 degrees sweptback circular-arc wing with a fuselage and with leading-edge and split flaps at a Reynolds number of 5,300,000
Year: 1947
Abstract: INTRODUCTION
Supersonic air-flow theory indicates the practicability of using wings with large angels of sweep and sharp-edge airfoil sections for flight at speeds above the speed of sound. in the low-speed range close to maximum lit, the stability of swept-wing aircraft cannot be adequately evaluated from existing theories and, consequently, experimental means of determining their characteristics must be used. Investigations were therefore made in the Langley 19-foot pressure tunnel to determine the aerodynamic characteristics of a 42° sweptback wing of symmetrical circular-are airfoil sections at a Reynolds number of 5,300,000 and mach number of 0.11. The longitudinal characteristics of this wing are presented in reference 1. This paper presents the aerodynamic characteristics of the wing in yaw and, also, shows the effects of various wing flaps and of a fuselage on these characteristics with the wing mounted at high and low positions. In order to acquire information concerning the effectiveness of a vertical tail on a swept-wing airplane, air-stream surveys were made to determine the side wash angles and dynamic-pressure ratios in the region of a vertical tail.
A comparison is shown of the lateral-stability parameters of the circular-arc wing and a wing of nearly identical plan form but employing NACA 641-112 airfoil sections.
Supersonic air-flow theory indicates the practicability of using wings with large angels of sweep and sharp-edge airfoil sections for flight at speeds above the speed of sound. in the low-speed range close to maximum lit, the stability of swept-wing aircraft cannot be adequately evaluated from existing theories and, consequently, experimental means of determining their characteristics must be used. Investigations were therefore made in the Langley 19-foot pressure tunnel to determine the aerodynamic characteristics of a 42° sweptback wing of symmetrical circular-are airfoil sections at a Reynolds number of 5,300,000 and mach number of 0.11. The longitudinal characteristics of this wing are presented in reference 1. This paper presents the aerodynamic characteristics of the wing in yaw and, also, shows the effects of various wing flaps and of a fuselage on these characteristics with the wing mounted at high and low positions. In order to acquire information concerning the effectiveness of a vertical tail on a swept-wing airplane, air-stream surveys were made to determine the side wash angles and dynamic-pressure ratios in the region of a vertical tail.
A comparison is shown of the lateral-stability parameters of the circular-arc wing and a wing of nearly identical plan form but employing NACA 641-112 airfoil sections.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:30:38Z | |
| date available | 2017-09-04T16:30:38Z | |
| date copyright | 01/01/1947 | |
| date issued | 1947 | |
| identifier other | UMMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/94037 | |
| description abstract | INTRODUCTION Supersonic air-flow theory indicates the practicability of using wings with large angels of sweep and sharp-edge airfoil sections for flight at speeds above the speed of sound. in the low-speed range close to maximum lit, the stability of swept-wing aircraft cannot be adequately evaluated from existing theories and, consequently, experimental means of determining their characteristics must be used. Investigations were therefore made in the Langley 19-foot pressure tunnel to determine the aerodynamic characteristics of a 42° sweptback wing of symmetrical circular-are airfoil sections at a Reynolds number of 5,300,000 and mach number of 0.11. The longitudinal characteristics of this wing are presented in reference 1. This paper presents the aerodynamic characteristics of the wing in yaw and, also, shows the effects of various wing flaps and of a fuselage on these characteristics with the wing mounted at high and low positions. In order to acquire information concerning the effectiveness of a vertical tail on a swept-wing airplane, air-stream surveys were made to determine the side wash angles and dynamic-pressure ratios in the region of a vertical tail. A comparison is shown of the lateral-stability parameters of the circular-arc wing and a wing of nearly identical plan form but employing NACA 641-112 airfoil sections. | |
| language | English | |
| title | NACA-RM-L7I30 | num |
| title | Yaw characteristics and sidewash angles of a 42 degrees sweptback circular-arc wing with a fuselage and with leading-edge and split flaps at a Reynolds number of 5,300,000 | en |
| type | standard | |
| page | 40 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1947 | |
| contenttype | fulltext |