درباره ما
NACA-TR-1274
Second-order subsonic airfoil theory including edge effects
Year: 1956
Abstract: Several recent advances in plane subsonic flow theory are combined into a unified second-order theory for airfoil sections of arbitrary shape. The solution is reached in three steps: the incompressible result is found by integration, it is converted into the corresponding subsonic compressible result by means of the second-order compressibility rule, and it is rendered uniformly valid near stagnation points by further rules. Solutions for a number of airfoils are given and are compared with the results of other theories and of experiment. A straight-forward computing scheme is outlined for calculating the surface velocities and pressures on any airfoil at any angle of attack
Subject: AERODYNAMICS
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:10:26Z | |
| date available | 2017-09-04T17:10:26Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | YPONEEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/133917 | |
| description abstract | Several recent advances in plane subsonic flow theory are combined into a unified second-order theory for airfoil sections of arbitrary shape. The solution is reached in three steps: the incompressible result is found by integration, it is converted into the corresponding subsonic compressible result by means of the second-order compressibility rule, and it is rendered uniformly valid near stagnation points by further rules. Solutions for a number of airfoils are given and are compared with the results of other theories and of experiment. A straight-forward computing scheme is outlined for calculating the surface velocities and pressures on any airfoil at any angle of attack | |
| language | English | |
| title | NACA-TR-1274 | num |
| title | Second-order subsonic airfoil theory including edge effects | en |
| type | standard | |
| page | 24 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMICS | |
| subject keywords | AIRFOIL PROFILES | |
| subject keywords | AIRFOILS | |
| subject keywords | ANGLE OF ATTACK | |
| subject keywords | APPROXIMATION | |
| subject keywords | COMPRESSIBILITY EFFECTS | |
| subject keywords | COMPUTATIONAL FLUID DYNAMICS | |
| subject keywords | FLOW CHARACTERISTICS | |
| subject keywords | INTEGRALS | |
| subject keywords | LEADING EDGES | |
| subject keywords | SUBSONIC FLOW | |
| subject keywords | THICKNESS RATIO | |
| subject keywords | THIN AIRFOILS |