Add to ORKGA method for evaluating the Glauert coefficients from airfoil pressure distributions is investigated. The linear operating range of the airfoils in steady-state and periodic operating conditions are considered. A rational method for quantitatively characterizing airfoil pressure distributions relative to their geometry and aerodynamic operating environment is developed. The characteristics of the airfoil operating environment is determined from its measured pressure distribution
M the request of the United States Army Air Service, the tests reported herein were con-ducted in th...
Pressure distributions determined from high-speed wind-tunnel tests are presented for five NACA airf...
Information is presented with which ordinates can be easily obtained for any thickness from 2 to 21 ...
This report gives the theoretical distribution of pressure at lift coefficients of 0, 0.5, 1.0, and ...
Surface pressure distributions were measured for the 13% thick GA(W)-2 airfoil section fitted with 2...
A method is presented for the rapid calculation of the pressure distribution over an airfoil section...
Measurements were made to determine the distribution of pressure over one section of an R. A. F. 30 ...
Report presents the results of wind tunnel tests made in the NACA 7 by 10-foot wind tunnel of a Clar...
Report presents the results of pressure-distribution tests of an NACA 23012 airfoil with an NACA 230...
This report deals with pressure distribution tests on an airfoil with a conventional trailing edge f...
By a generalization of the Joukowski method, a procedure is developed for effecting localized modifi...
In this report a theory of thin airfoils of small camber is developed which permits either the veloc...
Report presents the results of pressure-distribution of an NACA 23012 airfoil equipped with a slotte...
Report presents the results of tests made of a Clark y airfoil with a Clark y Fowler flap and of an ...
Measurements were made in the variable density wind tunnel to determine the pressure distribution ov...
M the request of the United States Army Air Service, the tests reported herein were con-ducted in th...
Pressure distributions determined from high-speed wind-tunnel tests are presented for five NACA airf...
Information is presented with which ordinates can be easily obtained for any thickness from 2 to 21 ...
This report gives the theoretical distribution of pressure at lift coefficients of 0, 0.5, 1.0, and ...
Surface pressure distributions were measured for the 13% thick GA(W)-2 airfoil section fitted with 2...
A method is presented for the rapid calculation of the pressure distribution over an airfoil section...
Measurements were made to determine the distribution of pressure over one section of an R. A. F. 30 ...
Report presents the results of wind tunnel tests made in the NACA 7 by 10-foot wind tunnel of a Clar...
Report presents the results of pressure-distribution tests of an NACA 23012 airfoil with an NACA 230...
This report deals with pressure distribution tests on an airfoil with a conventional trailing edge f...
By a generalization of the Joukowski method, a procedure is developed for effecting localized modifi...
In this report a theory of thin airfoils of small camber is developed which permits either the veloc...
Report presents the results of pressure-distribution of an NACA 23012 airfoil equipped with a slotte...
Report presents the results of tests made of a Clark y airfoil with a Clark y Fowler flap and of an ...
Measurements were made in the variable density wind tunnel to determine the pressure distribution ov...
M the request of the United States Army Air Service, the tests reported herein were con-ducted in th...
Pressure distributions determined from high-speed wind-tunnel tests are presented for five NACA airf...
Information is presented with which ordinates can be easily obtained for any thickness from 2 to 21 ...