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NACA-RM-L56J04
Effectiveness at transonic speeds of flap-type ailerons for several spanwise locations on a 4-percent-thick sweptback-wing-fuselage model with and without tails
Year: 1957
Abstract: INTRODUCTION
Experimental research at transonic speeds to determine lateral control characteristics of flap-type ailerons is needed because the available data are meager and theory is inadequate for accurate prediction control effectiveness. Most existing information has been obtained from tests of small-scale models by utilizing the transonic-bump and wingTechniques. (See, for example, refs. 1 to 3.) Accordingly, effectiveness and loading characteristics of flap-type controls on relatively large-scale unswept, sweptback, and delta wings are being investigated the Langley 16-foot transonic tunnel at Mach numbers up to and slightly above 1.0. Results from an unswept-wing model investigation are reported in reference 4. The present paper includes effectiveness information obtained from tests of a 450 sweptback-wing model with inboard, midspan, and outboard ailerons. In addition, the effects oaf horizontal tail, a vertical tail, and *he complete empennage on the lateral characteristics are included.
The sting-supported model used for the investigation 45° sweptback wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections streamwise. The longitudinal characteristics of this model without ailerons are presented in reference 5. For the present investigation the model was equipped with inboard, midspan, and outboard unbalanced ailerons, each having span of 40 percent of the wing semispan and a chord of 30 percent of the wing chord. Data have been obtained at Mach numbers from 0.80 to 1.03, angles of attack up to 27°, and aileron deflections to approximately +15°. The test Reynolds number was approximately 7 x 106.
Experimental research at transonic speeds to determine lateral control characteristics of flap-type ailerons is needed because the available data are meager and theory is inadequate for accurate prediction control effectiveness. Most existing information has been obtained from tests of small-scale models by utilizing the transonic-bump and wingTechniques. (See, for example, refs. 1 to 3.) Accordingly, effectiveness and loading characteristics of flap-type controls on relatively large-scale unswept, sweptback, and delta wings are being investigated the Langley 16-foot transonic tunnel at Mach numbers up to and slightly above 1.0. Results from an unswept-wing model investigation are reported in reference 4. The present paper includes effectiveness information obtained from tests of a 450 sweptback-wing model with inboard, midspan, and outboard ailerons. In addition, the effects oaf horizontal tail, a vertical tail, and *he complete empennage on the lateral characteristics are included.
The sting-supported model used for the investigation 45° sweptback wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections streamwise. The longitudinal characteristics of this model without ailerons are presented in reference 5. For the present investigation the model was equipped with inboard, midspan, and outboard unbalanced ailerons, each having span of 40 percent of the wing semispan and a chord of 30 percent of the wing chord. Data have been obtained at Mach numbers from 0.80 to 1.03, angles of attack up to 27°, and aileron deflections to approximately +15°. The test Reynolds number was approximately 7 x 106.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:04:50Z | |
| date available | 2017-09-04T17:04:50Z | |
| date copyright | 01/01/1957 | |
| date issued | 1957 | |
| identifier other | YAYIYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/128436 | |
| description abstract | INTRODUCTION Experimental research at transonic speeds to determine lateral control characteristics of flap-type ailerons is needed because the available data are meager and theory is inadequate for accurate prediction control effectiveness. Most existing information has been obtained from tests of small-scale models by utilizing the transonic-bump and wingTechniques. (See, for example, refs. 1 to 3.) Accordingly, effectiveness and loading characteristics of flap-type controls on relatively large-scale unswept, sweptback, and delta wings are being investigated the Langley 16-foot transonic tunnel at Mach numbers up to and slightly above 1.0. Results from an unswept-wing model investigation are reported in reference 4. The present paper includes effectiveness information obtained from tests of a 450 sweptback-wing model with inboard, midspan, and outboard ailerons. In addition, the effects oaf horizontal tail, a vertical tail, and *he complete empennage on the lateral characteristics are included. The sting-supported model used for the investigation 45° sweptback wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections streamwise. The longitudinal characteristics of this model without ailerons are presented in reference 5. For the present investigation the model was equipped with inboard, midspan, and outboard unbalanced ailerons, each having span of 40 percent of the wing semispan and a chord of 30 percent of the wing chord. Data have been obtained at Mach numbers from 0.80 to 1.03, angles of attack up to 27°, and aileron deflections to approximately +15°. The test Reynolds number was approximately 7 x 106. | |
| language | English | |
| title | NACA-RM-L56J04 | num |
| title | Effectiveness at transonic speeds of flap-type ailerons for several spanwise locations on a 4-percent-thick sweptback-wing-fuselage model with and without tails | en |
| type | standard | |
| page | 39 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1957 | |
| contenttype | fulltext |