"INTRODUCTION A computer program@ ESDUpac A9510@ has been prepared that uses steady lifting-surface theory based on the Multhopp-Richardson solution (Derivation 1) to provide the spanwise loading of wings with camber and twist in subsonic attached flow. The basic calculation core of the program is as reported in Derivation 2@ and this has been adapted to ESDUpac format@ with modified input and output routines. The program calculates the spanwise loading distributions of local lift and pitching moment due to incidence@ due to camber at zero incidence@ and due to twist at zero incidence. The loadings can be obtained individually or simultaneously. The overall loading distribution can be calculated for a specified incidence or total lift coefficient. This Item is a companion to Item No. 83040 (Reference 10) that gives a graphical means of obtaining the spanwise lift loading based on a correlation of numerous calculations by Multhopp's lifting-surface theory. In the cases of the camber and twist contributions the graphical method was based on runs of the program of Derivation 2@ although the method for the loading due to incidence was based on the predictions of a different encapsulation of Multhopp's theory@ see Reference 6. The program allows for either the input of a straight-tapered planform defined simply via aspect ratio@ taper ratio and nth-chord line sweep or the input of a cranked planform with straight leading-edge and trailing-edge segments. The details of how the geometry for the cranked wing is input are given subsequently. The program outputs a wing lift-curve slope@ a1 . This is taken from the program ESDUpac A7011@ described in Derivation 3@ that is incorporated in ESDUpac A9510 as a subroutine. The data in ESDUpac A7011 were based on calculations reported in Reference 9 that were made using the Multhopp-Garner lifting-surface solution. This ensures consistency with other aerodynamics Items (including Item No. 83040) and provides a slightly more accurate value for a1 than the Multhopp-Richardson solution. All the loading distributions and force and moment coefficients that are output by ESDUpac A9510 have been factored by the ratio of lift-curve slopes to incorporate this improvement in accuracy. Because ESDUpac A7011 applies only to a straight-tapered wing@ the estimation of the lift-curve slope for a cranked wing requires the program to make a prior calculation of an ""equivalent"" straight tapered wing by the method in Addendum A of Item No. 76003 (Derivation 4). This is the recommended procedure in Item No. 83040. Section 3 describes the necessary input and the options that may be selected when running the program. Table 3.1 summarises all the required input. Section 4 summarises the output. The accuracy and applicability are discussed in Section 5. The Derivation and References are given in Section 6. Input and output examples are given in Section 7."
ESDU 95010 B-1997 history
1997ESDU 95010 B-1997 COMPUTER PROGRAM FOR ESTIMATION OF SPANWISE LOADING OF WINGS WITH CAMBER AND TWIST IN SUBSONIC ATTACHED FLOW