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NACA-TR-1109
Experimental investigation of base pressure on blunt-trailing-edge wings at supersonic velocities
Year: 1952
Abstract: Measurements of base pressure are presented for 29 blunttrailing-edge wings having an aspect ratio of 3.0 and various airfoil profiles. The different profiles comprised thickness ratios between 0.05 and 0.10, boat tail angles between 2.90 and 200, and ratios of trailing-edge thickness to airfoil thickness between 0.2 and 1.0. The tests were conducted at mach numbers of 1.25,1.5,2.0, and 3.1. For each mach number, the Reynolds number and angle of attack were carried. The lowest Reynolds number investigated was 0.2 X106 and the highest was 3.5X106. Measurements on each wing were obtained separately with turbulent flow and laminar flow in the boundary layer. Spanwise surveys of the base pressure were conducted on several wings.
Subject: ANGLE
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:01:01Z | |
| date available | 2017-09-04T18:01:01Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | FYDZYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/184058 | |
| description abstract | Measurements of base pressure are presented for 29 blunttrailing-edge wings having an aspect ratio of 3.0 and various airfoil profiles. The different profiles comprised thickness ratios between 0.05 and 0.10, boat tail angles between 2.90 and 200, and ratios of trailing-edge thickness to airfoil thickness between 0.2 and 1.0. The tests were conducted at mach numbers of 1.25,1.5,2.0, and 3.1. For each mach number, the Reynolds number and angle of attack were carried. The lowest Reynolds number investigated was 0.2 X106 and the highest was 3.5X106. Measurements on each wing were obtained separately with turbulent flow and laminar flow in the boundary layer. Spanwise surveys of the base pressure were conducted on several wings. | |
| language | English | |
| title | NACA-TR-1109 | num |
| title | Experimental investigation of base pressure on blunt-trailing-edge wings at supersonic velocities | en |
| type | standard | |
| page | 19 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext | |
| subject keywords | ANGLE | |
| subject keywords | ANGLES | |
| subject keywords | ATTACK | |
| subject keywords | BASE | |
| subject keywords | BLUNT | |
| subject keywords | BOATTAILS | |
| subject keywords | BOUNDARY | |
| subject keywords | EDGES | |
| subject keywords | FLOW | |
| subject keywords | GEOMETRY | |
| subject keywords | LAMINAR | |
| subject keywords | LAYER | |
| subject keywords | MACH | |
| subject keywords | NUMBER | |
| subject keywords | PRESSURE | |
| subject keywords | PROFILES | |
| subject keywords | RATIO | |
| subject keywords | REYNOLDS | |
| subject keywords | SPAN | |
| subject keywords | SPEED | |
| subject keywords | SUPERSONIC | |
| subject keywords | TESTS | |
| subject keywords | THICKNESS | |
| subject keywords | TRAILING | |
| subject keywords | TUNNEL | |
| subject keywords | TURBULENT | |
| subject keywords | WIND | |
| subject keywords | WING | |
| subject keywords | WINGS |