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AIRFOILS AT LOW SPEEDS

Airfoils at Low Speeds
Copyright © 1989 by Selig, Donovan, and Fraser
All rights reserved
H. A. Stokely, publisher
1504 North Horseshoe Circle
Virginia Beach, Virginia 23451
USA
Airfoils at Low Speeds v
FOREWORD AND ACKNOWLEDGEMENTS
The history of this experimental program on low-speed airfoils is extensive.
In August 1986, work toward testing model sailplane airfoils in a wind tunnel at
Princeton University began on an ambitious scale. The initial plan was to test
30 airfoils: 15 existing airfoils and 15 new airfoils to be designed concurrently
with the tests. As news of the project caught the attention of radio control (RC)
model soaring enthusiasts, the project grew far beyond the original goals and
expectations, thanks to their generosity. When the experimental apparatus was
finally dismantled in January 1989, almost two and a half years later, over 60
models were tested and over 130 airfoil polars were generated. It is our hope
that the results of this work will be valuable to modelers and researchers for
many years to come.
A word is in order to explain the role each of us played in this effort. The
initial impetus for the project, its organization and day-to-day management,
as well as the wind tunnel testing and data reduction were done by Selig and
Donovan. They also designed all of the new airfoils except for the DF- series by
Fraser.
The custom measurement apparatus was built jointly by Selig and Donovan at
Princet.on University and by Fraser at Fraser-Volpe Corporation. The digitizing
of the models was done at Fraser-Volpe Corporation by Fraser, who also wrote
the computer programs for reducing this part of the data. All three of us shared
in the writing and editing of this book.
We would also like to mention that everything from the data collection to
the writing of this book was done by computer. There is not a single number
anywhere in any part of the data thiJ.t was generated, computed, reduced, copied,
averaged, printed, graphed, or manipulated by hand. Aside from the speed and
convenience of this approach, the principal advantage is the complete elimination
of several types of errors that may otherwise occur.
5i
All of the airfoil polar data is available on 3~ or inch IBM compatible
diskette from Fraser.
Sincere thanks go to Prof. Smits of the Princeton University Gas Dynamics
Laboratory for his enduring support while this extracurricular project began to
grow and consume seemingly endless hours of time away from the first two au
thors' regular thesis research. The gracious support of Prof. Lam and Prof. Cur
tiss of Princeton University, and the helpful discussions of Prof. Maughmer of
The Pennsylvania State University are appreciated. Thanks also go to Lou Piz
zarello who provided us with an air conditioner and new air intake filters for the
tunnel.
We are indebted to Ray Olsen for his many contributions at times when we
needed them most.
vi Airfoils at Low Speeds
For monetary contributions which made possible the purchase of important el
ements essential to this work we thank Rolf Girsberger, H.A. Stokely, Jerry Jack
son, Armin Saxer, Charles Griswald, C. Haverlan, H.J. Rogers, Preben Norholm,
Brian Smith, Thomas Yamokoski, and Trey Wood.
The expertise of many skilled model builders made the lengthy set-up stage
all worthwhile. In this respect we very deeply appreciate the work of Bob
Champine, Ron Wagner, Stan Watson, Mark Allen, Michael Bame, Tony Beck,
Woody Blanchard, Charles Fox, Peter Illick, Harley Michaelis, Forrest Miller,
Ted Off, Mike Reed, Tyson Sawyer, Chuck Anderson, Norman Anderson, Jerry
Arana, Bruce Baker, Ken Bates, David Batey Jr., Rich Border, John Boren,
Mike Chiddick, Doug Dorton, Roger Egginton, Dale Folkening, Harlan Halsey,
John Hohensee, Dave Jones, Stan Koch, Terry Luckenbach, Carl Mohs, Lee Mur
ray, Mark Nankivil, R.J. Ostrander, Jef Raskin, Les Rogers, Joe Ruminski, and
Karl Widiner.
Prof. Mark Drela of M.I.T. is gratefully acknowledged for making his ISES
computer code available to aid in the analysis of the new airfoil designs. Finally,
MKS Instruments, Inc. and Scientific Solutions, Inc. are acknowledged for their
valuable contributions of instrumentation.
Airfoils at Low Speeds vii
TABLE OF CONTENTS
Foreword and Acknowledgements . . v
List of Polars and Lift Plots viii
List of Symbols and Abbreviations xii
1 Introduction . . . . . . . . 1
2 Experimental Facility and Measurement Technique 5
2.1 Flow Quality . . . . 5
2.2 Wind Tunnel Models 6
2.2.1 Digitized Profiles 7
2.2.2 Digitizing Procedure 7
2.2.3 Digitizer Res1,1lts 9
2.3 Force Measurement Technique and Instrumentation 11
2.4 Comparison with Other Facilities 16
3 Low Reynolds Number Terminology 41
3.1 Laminar Separation Bubbles 41
3.2 Trips and Bubble Ramps . . . 42
3.3 Airfoil Hysteresis . . . . . . 42
4 Project Design Methods and Goals 45
5 Comments on Airfoils 51
5 .1 Airfoil Discussions 53
5.2 Stall Behavior 88
5.3 Trips and Surface Roughness 89
5.4 Trailing Edge Thickness 90
5.5 Surface Waviness and Contour Accuracy 90
6 References . . . . 101
7 Airfoil Coordinates 103
7.1 Nominal 103
7.2 Actual .... 129
8 Predicted Moment Data 147
9 Airfoil Thickness and Camber 149
10 Digitizer Plots . . . . . 153
11 Airfoil Comparison Plots 187
12 Airfoil Polars and Lift Plots 193
13 Tabulated Polar Data 359
14 Addresses . . . . . . . . 397
viii Airfoils at Low Speeds
LIST OF POLARS AND LIFT PLOTS
Figure
12.1 AQUILA-PT 193
12.2 AQUILA-PT lift data 194
12.3 CLARK-Y-PT ·. . . 195
12.4 CLARK-Y-PT lift data 196
12.5 DAE51-PT 197
12.6 DAE51-PT thickened trailing edge 198
12.7 DAE51-PT lift data 199
12.8 DF101-PT 200
12.9 DF102-PT 201
12.10 DF103-PT 202
12.11 E193-PT . 203
12.12 E193MOD-PT 204
12.13 E205A-PT . . 205
12.14 E205B-PT . . 206
12.15 E205B-PT lift data 207
12.16 E214A-PT . . . 208
12.17 E214B-PT . . . 209
12.18 E214C-PT 3° flap 210
12.19 E214C-PT 0° flap 211
12.20 E214C-PT -3° flap 212
12.21 E214C-PT -6° flap 213
12.22 E214C-PT u.s.t. xjc = 20%,hjc = .17%,w/c = 1.0% 214
12.23 E214C-PT lift data 215
12.24 E374A-PT . . . . . . . . . . . . . . 216
12.25 E374B-PT . . . . . . . . . . . . . . 217
12.26 E374B-PT u.s. bumps xjc =50%, type A 218
12.27 E374B-PT u.s.t. xjc = 20%,hjc = .17%,w/c = 1.0% 219
12.28 E374B-PT u.s. wavy clay, xjc = O% to 15%,h/c = .20% 220
12.29 E374B-PT thickened trailing edge 221
12.30 E374B-PT lift data 222
12.31 E387 A-PT . . . . . . . . . . 223
12.32 E387 A-PT repeated . . . . . . 224
12.33 E387 A-PT u.s.t. xjc = 20%, hjc = 0.17%, wjc = 1.0% 225
12.34 E387 A-PT high turbulence 226
12.35 E387 A-PT lift data 227
12.36 E387B-PT . . . . . 228
12.37 Flat Plate-PT 229
12.38 Flat Plate-PT lift data 230
12.39 FX60-l00-PT . . . . 231
Airfoils at Low Speeds ix
12.40 FX63-137 A-PT 232
12.41 FX63-137B-PT 233
12.42 HQ2/9A-PT 234
12.43 HQ2/9A-PT u.s.t. xjc = 20%,hjc = .17%,wjc = 1.0% 235
12.44 HQ2/9A-PT u.s.t. xjc = 40%, h/c = .17%,wjc = 1.0% 236
12.45 HQ2/9A-PT l.s.t. xjc = 50%,h/c = .17%,wjc = 1.0% 237
12.46 HQ2/9A-PT lift data . . . . . . . . . . . . . . 238
12.47 HQ2/9B-PT . . . . . . . . . . . . . . . . .. 239
12.48 HQ2/9B-PT u.s.t. xjc = 50%,hjc = .17%,wjc = 1.0% 240
12.49 HQ2/9B-PT u.s. blowing xjc =50%, type B 241
12.50 HQ2/9B-PT trips, Rn = 200,000 242
12.51 HQ2/9B-PT lift data 243
12.52 J5012-PT . . . . . . . . . . 244
12.53 MB253515-PT . . . . . . . . 245
12.54 MB253515-PT u.s.t. xjc = 20%,hjc = .17%,w/c = 1.0% 246
12.55 MB253515-PT lift data . . . . . . . . . . 247-249
12.56 M0&-13-128-PT . . . . . . . . . . . . . . . . . . 250
12.57 M0&-13-128-PT u.s. bumps xjc = 31%, type A .... 251
12.58 M0&-13-128-PT misc. u.s. trips, xjc = 31%,Rn = 200,000 252
12.59 M0&-13-128-PT lift data 253
12.60 NACA 0009-PT .... 254
12.61 NACA 0009-PT lift data 255
12.62 NACA 2.5411-PT . . . 256
12.63 NACA 2.5411-PT lift data 257
12.64 NACA 64A010-PT 258
12.65 NACA 64A010-PT lift data 259
12.66 NACA 6409-PT . . . . 260
12.67 NACA 6409-PT lift data . 261
12.68 RG15-PT . . . . . . . 262
12.69 RG15-PT u.s.t. xjc = 20%,hjc = .17%,wjc = 1.0% 263
12.70 RG15-PT u.s.t. x/c = 40%,hjc = .17%,wjc = 1.0% 264
12.71 RG15-PT u.s.t. x/c = 60%,hjc = .17%,wjc = 1.0% 265
12.72 RG15-PT u.s.t. xjc = 70%,h/c = .17%,wjc = 1.0% 266
12.73 RG15-PT lift data 267
12.74 52048-PT . . . . . 268
12.75 52048-PT with trips . 269
12.76 52048-PT misc. trips 270
12.77 52048-PT lift data 271
12.78 52055-PT 272
12.79 52091A-PT ... 273
12.80 52091B-PT . . . 274
12.81 52091B-PT Gurney Flap type A 275
x Airfoils at Low Speeds
12.82 82091B-PT Gurney Flap type B 276
12.83 82091B-PT Gurney Flap type C 277
12.84 82091B-PT lift data 278
12.85 83010-PT 279
12.86 83010-PT lift data 280
12.87 83014-PT 281
12.88 83014-PT lift data 282
12.89 83016-PT 283
12.90 83021A-PT . . . 284
12.91 83021A-PT lift data 285
12.92 83021B-PT 286
12.93 84061A-PT . . . . 287
12.94 84061B-PT . . . . 288
12.95 84061B-PT u.s.t. xfc = 45%,hfc = .17%,w/c = 1.0% 289
12.96 84061B-PT u.s.t. xfc = 45%, Rn = 150,000 .... 290
12.97 84061B-PT u.s.t. xfc = 45%, Rn = 150,000 and 300,000 291
12.98 84061B-PT lift data 292
12.99 84062-PT 293
12.100 84180-PT . . . . 294
12.101 84233-PT . . . . 295
12.102 84233-PT u.s.t. xfc = 20%,hfc = .17%,wfc = 1.0% 296
12.103 84233-PT lift data . 297
12.104 8D2030-PT . . . . 298
12.105 8D2030-PT lift data 299
12.106 8D2083-PT . . . . 300
.
12.107 8D5060-PT 301
•'
12.108 8D5060-PT lift data 302
12.109 8D6060-PT . . . . 303
12.110 8D6060-PT u.s.t. xfc = 20%,h/c = .17%,w/c = 1.0% 304
12.111 SD6060-PT u.s.t. xjc = 40%,hjc = .17%,w/c = 1.0% 305
12.112 SD6060-PT lift data . . . . . . . . . . . . . . 306
12.113 8D6080-PT . . . . . . . . . . . . . . . . . . 307
12.114 8D6080-PT u.s.t. xfc = 10%,hjc = .17%,wjc = 1.0% 308
12.115 8D6080-PT u.s.t. xfc = 20%,hjc = .17%,wjc = 1.0% 309
12.116 8D6080-PT u.s.t. xfc = 30%,hjc = .17%,w/c = 1.0% 310
12.117 8D6080-PT thickened trailing edge 311
12.118 8D7003-PT . . . . . . . . . . . . . . . . . . 312
12.119 8D7003-PT repeated . . . . . . . . . . . . . . 313
12.120 8D7003-PT u.s.t. xfc = 60%,hfc = .17%,wfc = 1.0% 314
12.121 8D7003-PT u.s.t. xfc = 70%,hjc = .17%,wfc = 1.0% 315
12.122 8D7003-PT u.s. bumps xfc =50%, type A 316
12.123 SD7003-PT u.s. bumps xfc = 60%, type A .... 317
Airfoils at Low Speeds xi
12.124 SD7003-PT u.s. bumps xjc = 70%, type A 318
12.125 SD7003-PT lift data 319
12.126 SD7032A-PT 320
12.127 SD7032B-PT 321
12.128 SD7032C-PT 6° flap 322
12.129 SD7032C-PT 3° flap 323
12.130 SD7032C-PT 0° flap 324
12.131 SD7032CcPT -3° flap 325
12.132 SD7032C-PT -6° flap 326
12.133 SD7032C-PT lift data 327
12.134 SD7032D-PT . . . . 328
= =
12.135 SD7032D-PT u.s.t. xjc 45%,hjc .17%,wjc = 1.0% 329
12.136 SD7037-PT . . . . . . . . . . . . . . . . . . 330
12.137 SD7037-PT u.s.t. xjc = 30%,hjc = .17%,wjc = 1.0% 331
12.138 SD7043-PT . . . . . . . . . . . . . . . . . . 332
= = =
12.139 SD7043-PT u.s.t. xjc 20%,hjc .17%,w/c 1.0% 333
12.140 SD7043-PT lift data . . . . . . . . . . . . . . 334
12.141 SD7062-PT . . . . . . . . . . . . . . . . . . 335
12.142 SD7062-PT u.s.t. xjc = 15%,hjc = .17%,w/c = 1.0% 336
= = =
12.143 SD7062-PT u.s.t. xj c 15%, h/ c .08%, .17%, w / c 1.0% 337
12.144 SD7080-PT . . . . 338
12.145 SD7080-PT lift data 339
12.146 SD7084-PT . . . . 340
12.147 SD7084-PT lift data 341
12.148 SD7090-PT . . . . 342
12.149 SD7090-PT loose/tight covering, Rn = 300,000 343
12.150 SD7090-PT trips, Rn = 300,000 344
12.151 SD7090-PT lift data . . . . . . . . . . . . 345
12.152 SD8000-PT . . . . . . . . . . . . . . . . 346
12.153 SD8000-PT u.s.t. xjc = 20%,hjc = .17%,w/c = 1.0% 347
12.154 SD8000-PT u.s.t. xjc = 40%,hjc = .17%,w/c = 1.0% 348
12.155 SD8000-PT u.s.t. xjc = 70%,hjc = .17%,w/c = 1.0% 349
12.156 SD8000-PT lift data 350
12.157 SD8020-PT . . . . 351
12.158 SD8020-PT lift data 352
12.159 SD8040-PT 353
12.160 SPICA-PT 354
12.161 SPICA-PT lift data 355
12.162 WB135/35-PT . . 356
12.163 WB135/35-PT lift data 357
12.164 WB140/35/FB-PT . . 358