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NACA-WR-L-701
Test of NACA 66, 2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane
Year: 1942
Abstract: INTRODUCTION
At the request of the Army Air Forces, Materiel Command, tests have been made in the Langley two-dimensional low-turbulence pressure tunnel of a model of the NACA 66,2-116, a = 0,6 airfoil section representing the root section of the wing for the XP-63 airplane.
The data presented in this report consist of the following:
(a) Lift, drag, and flap hinge-moment characteristics for the internal, balanced flap.
(b) Lift, drag, and flap hinge-moment characteristics for the "modified" internal balanced flap.
(c) Lift and drag characteristics for the slotted flap.
The model was of 24-inch chord (cw), built of wood with dural slot cover plates for the flap. All flaps were equipped with pressure orifices.
At the request of the Army Air Forces, Materiel Command, tests have been made in the Langley two-dimensional low-turbulence pressure tunnel of a model of the NACA 66,2-116, a = 0,6 airfoil section representing the root section of the wing for the XP-63 airplane.
The data presented in this report consist of the following:
(a) Lift, drag, and flap hinge-moment characteristics for the internal, balanced flap.
(b) Lift, drag, and flap hinge-moment characteristics for the "modified" internal balanced flap.
(c) Lift and drag characteristics for the slotted flap.
The model was of 24-inch chord (cw), built of wood with dural slot cover plates for the flap. All flaps were equipped with pressure orifices.
Subject: AIRFOILS
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:32:21Z | |
| date available | 2017-09-04T15:32:21Z | |
| date copyright | 01/01/1942 | |
| date issued | 1942 | |
| identifier other | AXITDEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/33978 | |
| description abstract | INTRODUCTION At the request of the Army Air Forces, Materiel Command, tests have been made in the Langley two-dimensional low-turbulence pressure tunnel of a model of the NACA 66,2-116, a = 0,6 airfoil section representing the root section of the wing for the XP-63 airplane. The data presented in this report consist of the following: (a) Lift, drag, and flap hinge-moment characteristics for the internal, balanced flap. (b) Lift, drag, and flap hinge-moment characteristics for the "modified" internal balanced flap. (c) Lift and drag characteristics for the slotted flap. The model was of 24-inch chord (cw), built of wood with dural slot cover plates for the flap. All flaps were equipped with pressure orifices. | |
| language | English | |
| title | NACA-WR-L-701 | num |
| title | Test of NACA 66, 2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane | en |
| type | standard | |
| page | 20 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1942 | |
| contenttype | fulltext | |
| subject keywords | AIRFOILS | |
| subject keywords | BALANCED | |
| subject keywords | BELL | |
| subject keywords | CHAR | |
| subject keywords | DIM | |
| subject keywords | DISTRIBUTION | |
| subject keywords | DRAG | |
| subject keywords | FLAPS | |
| subject keywords | HINGE | |
| subject keywords | LOW | |
| subject keywords | MOMENTS | |
| subject keywords | NACA | |
| subject keywords | PRESSURE | |
| subject keywords | SLOT | |
| subject keywords | SLOTTED | |
| subject keywords | TESTS | |
| subject keywords | TUNNEL | |
| subject keywords | TURBULENCE | |
| subject keywords | WIND | |
| subject keywords | WING | |
| subject keywords | WINGS |