Airfoil: RG15 (B) Builder: B. Champine Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61100 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -6.86 -0.487 0.0540 0.0651 0.0565 0.0373 0.0572 -4.99 -0.356 0.0286 0.0330 0.0335 0.0235 0.0243 -3.58 -0.251 0.0198 0.0304 0.0172 0.0149 0.0166 -1.93 -0.128 0.0153 0.0189 0.0169 0.0141 0.0114 -0.34 -0.009 0.0143 0.0078 0.0158 0.0220 0.0117 1.12 0.166 0.0169 0.0246 0.0117 0.0211 0.0104 2.76 0.444 0.0176 0.0143 0.0132 0.0248 0.0182 4.24 0.595 0.0186 0.0199 0.0171 0.0212 0.0163 5.66 0.708 0.0197 0.0197 0.0180 0.0248 0.0162 7.31 0.830 0.0251 0.0223 0.0199 0.0298 0.0283 8.86 0.935 0.0327 0.0257 0.0279 0.0435 0.0337 10.25 0.997 0.0451 0.0309 0.0463 0.0665 0.0368 Tabulated from data in file JG00085.DAT & reduced using program Q01.00L Average Reynolds #: 101200 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -6.45 -0.566 0.0390 0.0429 0.0402 0.0352 0.0376 -4.97 -0.407 0.0237 0.0237 0.0246 0.0232 0.0235 -3.47 -0.276 0.0149 0.0153 0.0154 0.0144 0.0146 -2.04 -0.195 0.0124 0.0129 0.0116 0.0099 0.0150 -0.47 -0.063 0.0123 0.0111 0.0102 0.0155 0.0124 1.10 0.217 0.0157 0.0155 0.0152 0.0165 0.0156 2.62 0.408 0.0143 0.0142 0.0149 0.0143 0.0138 4.10 0.520 0.0149 0.0144 0.0136 0.0156 0.0158 5.66 0.659 0.0170 0.0166 0.0162 0.0161 0.0191 7.23 0.802 0.0223 0.0200 0.0219 0.0239 0.0235 8.77 0.895 0.0294 0.0270 0.0279 0.0330 0.0295 10.28 0.925 0.0466 0.0423 0.0430 0.0539 0.0471 Tabulated from data in file JG00083.DAT & reduced using program Q01.00L Average Reynolds #: 151800 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -6.07 -0.425 0.0315 0.0306 0.0315 0.0328 0.0311 -5.10 -0.350 0.0219 0.0221 0.0211 0.0228 0.0214 -4.13 -0.270 0.0169 0.0172 0.0171 0.0179 0.0155 -3.25 -0.193 0.0137 0.0138 0.0137 0.0144 0.0129 -2.02 -0.090 0.0125 0.0114 0.0117 0.0148 0.0121 -1.28 -0.029 0.0120 0.0092 0.0133 0.0149 0.0108 0.04 0.173 0.0106 0.0111 0.0108 0.0110 0.0095 0.92 0.301 0.0100 0.0109 0.0092 0.0101 0.0098 2.01 0.421 0.0103 0.0111 0.0098 0.0102 0.0101 2.91 0.511 0.0112 0.0110 0.0101 0.0122 0.0117 4.07 0.629 0.0117 0.0120 0.0115 0.0116 0.0118 5.11 0.727 0.0133 0.0134 0.0127 0.0137 0.0133 5.95 0.799 0.0156 0.0158 0.0152 0.0157 0.0156 7.15 0.899 0.0195 0.0194 0.0177 0.0213 0.0198 8.20 0.966 0.0223 0.0214 0.0225 0.0228 0.0224 8.98 1.008 0.0277 0.0267 0.0268 0.0291 0.0283 10.00 1.054 0.0378 0.0378 0.0370 0.0390 0.0375 Tabulated from data in file AB00550.DAT & reduced using program Q01.00L Average Reynolds #: 202500 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -6.46 -0.424 0.0327 0.0317 0.0333 0.0340 0.0318 -5.09 -0.320 0.0183 0.0179 0.0181 0.0198 0.0173 -3.53 -0.188 0.0132 0.0128 0.0132 0.0144 0.0123 -1.98 -0.038 0.0113 0.0127 0.0110 0.0119 0.0096 -0.47 0.157 0.0093 0.0114 0.0047 0.0105 0.0106 1.13 0.334 0.0089 0.0102 0.0067 0.0089 0.0099 2.68 0.495 0.0093 0.0096 0.0087 0.0096 0.0093 4.20 0.647 0.0107 0.0107 0.0099 0.0113 0.0110 5.74 0.789 0.0136 0.0137 0.0129 0.0140 0.0139 7.27 0.912 0.0177 0.0181 0.0171 0.0180 0.0179 8.76 1.003 0.0247 0.0240 0.0236 0.0261 0.0250 10.31 1.066 0.0385 0.0387 0.0367 0.0403 0.0382 Tabulated from data in file JG00081.DAT & reduced using program Q01.00L Average Reynolds #: 302700 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -6.49 -0.458 0.0344 0.0332 0.0349 0.0349 0.0345 -5.14 -0.345 0.0157 0.0150 0.0149 0.0174 0.0154 -3.66 -0.209 0.0126 0.0121 0.0108 0.0165 0.0111 -2.16 -0.020 0.0091 0.0088 0.0086 0.0094 0.0096 -0.56 0.160 0.0083 0.0068 0.0087 0.0107 0.0068 0.94 0.319 0.0074 0.0066 0.0081 0.0079 0.0069 2.57 0.501 0.0078 0.0078 0.0077 0.0076 0.0080 4.06 0.657 0.0094 0.0095 0.0092 0.0096 0.0094 5.60 0.802 0.0121 0.0120 0.0112 0.0128 0.0123 7.16 0.935 0.0150 0.0152 0.0143 0.0156 0.0151 8.77 1.043 0.0219 0.0216 0.0203 0.0236 0.0220 10.36 1.112 0.0344 0.0339 0.0334 0.0367 0.0339 Tabulated from data in file AB00079.DAT & reduced using program Q01.00L File rg15b.drg created on 12-05-1997 at 15:25:59 using program FORMAT