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NACA-TR-1274

Second-order subsonic airfoil theory including edge effects

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T17:10:26Z
date available2017-09-04T17:10:26Z
date copyright01/01/1956
date issued1956
identifier otherYPONEEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/133917
description abstractSeveral 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
languageEnglish
titleNACA-TR-1274num
titleSecond-order subsonic airfoil theory including edge effectsen
typestandard
page24
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1956
contenttypefulltext
subject keywordsAERODYNAMICS
subject keywordsAIRFOIL PROFILES
subject keywordsAIRFOILS
subject keywordsANGLE OF ATTACK
subject keywordsAPPROXIMATION
subject keywordsCOMPRESSIBILITY EFFECTS
subject keywordsCOMPUTATIONAL FLUID DYNAMICS
subject keywordsFLOW CHARACTERISTICS
subject keywordsINTEGRALS
subject keywordsLEADING EDGES
subject keywordsSUBSONIC FLOW
subject keywordsTHICKNESS RATIO
subject keywordsTHIN AIRFOILS


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