~~ N A S A C O N T R A C T O R K-2835 R E P O R T m cr) 00 N =I U 4 m U z ANALYSIS AND COMPILATION OF MISSILE AERODYNAMIC DATA - Volume I Data Presentation and Analysis James 0,N ichols Prepared by AUBURN UNIVERSITY Auburn, Ala. 36830 jor Langley Research Center NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, 0. C. MAY 1977 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA CR-2835 4. Title and Subtitle 5. Report Date - ANALYSIS AND COMPILATION OF MISSILE AERODYNAMIC DATA VOLUME I May 1977 DATA PRESENTATION AND ANALYSIS I 6. Performing Organization Code 7. Author(r1 0. Performing Organization Report No. James 0. Nichols 10. Work Unit No. 9. PerformingO rganization Name and Address Aerospace Engineering Department Auburn University 11. Contract or Grant No. Auburn, Alabama 36830 NSG 1002 13. Type of Report and Period Covered 2. Sponsoring Agency Name and Address Contractor Report National Aeronautics and Space Administration Langley Research Center 14. Sponsoring Agency Code Hampton, VA 23365 7. Key Words (Suggested by Author(s)) 18. Distribution Statement Mis si1 e s - Mis si1 e Configurations Unclassified Unlimited Missile Performance Subject Category 02 9. Security Classif. (of this report) ' 20. Security Classif. (of this page) 21. NO. of psges 22. Rice' Unci assi f ied Unclassified 124 $5.50 FOREWORD The declassification of a number of technical documents which con- tain missile aerodynamic data and the need to facilitate the dissemina- tion of this data to potential users prompted the work reported herein. It was felt that the task could have educational benefits to senior level aerospace engineering students and could be incorporated into their regular academic work. Those students who participated received academic credit for Aeronautical Problems 1 and 2; Aerospace Design 1 and 2; and Missile.Aerodynamics. Participation was on a volunteer basis since the Problems and Design courses are individual effort type laboratory courses and Missile Aerodynamics is a senior level technical elective. Altogether some 15 to 20 students have been involved. A grant from the National Aeronautics and Space Administration pro- vided the necessary funds for class materials, field trips, and for preparation and publication of the report. Mr. Leroy Spearman of NASA's Langley Research Center has served as Technical Officer for this grant and provided the documents which were used. This final report, Analysis and Compilation of Missile Aerodynamic Data, is presented in two volumes. Volume I contains the analysis and compilation of data and Volume 11, which w i l l be compiled by Dr. John E. Burkhalter, w i l l contain the results of some performance analyses based on the data. An interim report was submitted December 31, 1974, which contained a compilation of the longitudinal data. The interim report has received iii some distribution, thus some errors that exist in that report and in the original technical documents w i l l be pointed out here. These errors have been corrected in this final report. A typographical error in the ABSTRACT of the Interim Report . lists the pitch control effectiveness as C It should m a . be Cm 6 The model drawing from TM X-3070 shown in the Interim Report shows the distance from the nose to the canard hinge line to be 12.60 centimeters. It should be 15.60 centimeters. The plot of Cm for TM X-3070 is incorrect in both the Interim 6 Report and TM X-3070. The data shown bases the pitching moment coefficient on body length instead of body diameter as stated in SYMBOLS. The plot of Cm in this final report 6 has been corrected to use body diameter as the reference length. The aerodynamic-center locations, X /a, were shown as per- ac centages for the configurations in TM X-1839, TM X-2289, and TM X-2491 in the Interim Report. The summary plot of longitudinal parameters in TM X-1332 and the Interim Report incorrectly show Cm to be negative. 6 The conversion of reference area and length were inadver- tently omitted for C in the summary plot of data from m6 RM L58C19 in the Interim Report. The decimal point was omitted in the base axial-force coef- ficient data in TM X-2367. The summary data have been checked a number of times in order to reduce the number of errors which wlll appear in this final report. Finally, I want to express my appreciation to Mrs. Marjorie McGee, secretary in the Aerospace Engineering Department, Auburn University, for typing this report. Auburn, Alabama James 0. Nichols V SUMMARY This summary document was prepared in order to facilitate dissemina- tion of a large amount of missile aerodynamic data which has recently been declassified. Only summary data are presented in this report, but a list of reference documents provides sources of detailed data. Most of the configurations considered are suitable for highly maneuverable air-to-air or surface-to-air missiles; however, data for a few air-to-surface, cruise missile, and one projectile configuration are also presented. The Mach number range of the data is from about 0.2 to 4.63; how- ever, data for most configurations cover only a portion of this range. The following aerodynamic characteristics at various Mach numbers and zero angle of attack are presented: a) Base drag coefficient, ‘D,b’ b) Drag coefficient, CDs0. . c) Lift-curve slope, CL a d) Aerodynamic-center location, Xac/a. . , e) Sideslip derivatives, C CaB, and Cy nB B . , , f) Control effectiveness, C C C ,. and Cy m6 n6 6 The maximum lift-drag ratio is also presented for some configurations. vi TABLE OF CONTENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . FOREWORD.. iii . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SUMMARY vi SYMBOLS............................... ix . . . . . . . . . . . . . . . . . . . . . . . . . . INTRODUCTION.. 1 . . . . . . . . . . . . . . . . . . . . . . . . APPARATUS AND TESTS 2 . . . . . . . . . . . . . . . . . . . . METHOD OF DATA PRESENTATION 3 . . . . . . . . . . . . . . . . . . . . . . . . . . DATAANALYSIS.. 6 . . . . . . . . . . . . . . . . . . . . . SUMMARY OF CONFIGURATIONS. 9 . . . . . . . . . . . . . . . . . . . . . . . . . DATASUMMARIES.. 16, . . . . . . . . . . . . . . . . . . . . LIST OF DOCUMENTS SUMMARIZED 105 vii SYMBOLS A body maximum cross-sectional area, .rrd2/4 Axial force I axial-force coefficient, cA qA Drag drag coefficient, cD qA Base drag at a=Oo base drag coefficient at a=O O, qA drag coefficient at a=O0 'D,o Lift lift coefficient, - cL qA lift-curve slope at a=Oo, per deg. cL a Rolling moment I cR rolling-moment coefficient, I qAd , effective-dihedral parameter, per deg. lateral (roll) control effectiveness, per deg. i Pitching moment pitching-moment coefficient, m' qAd slope of pitching-moment curve at a=Oo, per deg. I m' Ci C pitch control effectiveness at a=Oo, per deg. m6 Normal force normal-force coefficient, cN qA normal-force-curve slope at a=Oo, per deg. cN I a variation of normal-force coefficient with pitch control 1 cN6 surface deflection at a=Oo, per deg. Yawing moment C yawing-moment coefficient, n qAd I I C directional stability parameter, per deg. I nB C directional control effectiveness, per deg. "6 Side force side-force coefficient, SA ix side-force parameter, per deg. variation of side-force coefficient with directional control surface deflection, per deg. maximum body diameter maximum lift-drag ratio body length free-stream Mach number mass-flow ratio free-stream dynamic pressure orthogonal set of body axes orthogonal set of stability axes aerodynamic-center of l i f t location referenced to body length, positive aft from the nose moment center location referenced to body length, positive aft from the nose angle of attack, deg. . sideslip angle, deg angle of control surface deflection, positive trailing edge down or to left looking upstream, deg. angle of roll, deg. Subscripts : a aileron C canard F flap roll indicates deflection of lateral control surfaces W wing Yaw indicates deflection of directional control surfaces Subscripts are used when there may be some confusion about which control surface is being deflected. X INTRODUCTION Recently a number of technical documents containing missile aero- dynamic data published by the Langley Research Center of the National Aeronautics and Space Administration have been declassified. In order to facilitate dissemination of the data contained in these documents, this summary report was prepared. It was not intended that all of the original data be included, only summary plots of curve slopes and data suitable for comparison of the relative merits of the various configura- tions considered. A list of the reference documents is included to provide a source of more detailed data for configurations of interest. Some of the documents summarized were not previously classified but were included to give a more complete coverage of the configurations that have been tested at Langley. In all, thirty documents have been sum- marized. Some of these were themselves compilations of data that had been reported previously. Data from one of the documents, TM X-348, has not been included herein because of its limited scope, and because of the difficulty in presenting summary data for the numerous configurations tested. It is primarily a report of a parametrfc study of the static stability characteristics of a series of cone-cylinder bodies with various afterbody configurations-flares, fins, and boattails. Most of the configurations reported herein are suitable for highly maneuverable air-to-air or surface-to-air missiles; however, data for a few air-to-surface, cruise missile, and one projectile configuration are