Airfoil: S7075 (B) Builder: J. Thomas Comment: flap = 0 degs Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.22 -0.301 0.0269 0.0287 0.0239 0.0266 0.0283 -4.10 -0.231 0.0236 0.0262 0.0227 0.0229 0.0225 -3.11 -0.156 0.0180 0.0181 0.0165 0.0189 0.0185 -2.12 -0.073 0.0164 0.0199 0.0155 0.0148 0.0155 -1.05 0.030 0.0163 0.0212 0.0159 0.0140 0.0140 -0.04 0.152 0.0189 0.0228 0.0174 0.0171 0.0184 0.97 0.314 0.0254 0.0278 0.0287 0.0223 0.0229 2.00 0.483 0.0287 0.0299 0.0308 0.0265 0.0276 3.04 0.627 0.0248 0.0287 0.0229 0.0208 0.0267 4.07 0.734 0.0238 0.0234 0.0206 0.0189 0.0323 5.08 0.824 0.0221 0.0214 0.0226 0.0191 0.0254 6.16 0.905 0.0230 0.0237 0.0221 0.0234 0.0226 7.13 0.988 0.0306 0.0379 0.0320 0.0262 0.0262 8.18 1.072 0.0354 0.0423 0.0371 0.0317 0.0305 9.18 1.133 0.0358 0.0385 0.0369 0.0357 0.0319 10.14 1.181 0.0428 0.0492 0.0435 0.0390 0.0395 Tabulated from data in file CL01109.INT & reduced using program INTERP Average Reynolds #: 99800 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.19 -0.274 0.0350 0.0344 0.0356 0.0340 0.0358 -4.18 -0.199 0.0250 0.0246 0.0245 0.0254 0.0255 -3.11 -0.098 0.0208 0.0187 0.0220 0.0196 0.0228 -1.98 0.051 0.0167 0.0152 0.0179 0.0147 0.0189 -1.09 0.159 0.0149 0.0141 0.0151 0.0150 0.0154 -0.06 0.318 0.0158 0.0158 0.0154 0.0156 0.0161 0.97 0.458 0.0168 0.0170 0.0165 0.0162 0.0176 2.00 0.580 0.0173 0.0178 0.0170 0.0172 0.0172 3.05 0.680 0.0171 0.0192 0.0168 0.0160 0.0163 4.04 0.771 0.0168 0.0174 0.0172 0.0170 0.0156 5.12 0.869 0.0164 0.0174 0.0168 0.0162 0.0154 6.10 0.959 0.0174 0.0181 0.0189 0.0166 0.0159 7.11 1.045 0.0200 0.0204 0.0214 0.0196 0.0187 8.13 1.101 0.0252 0.0265 0.0264 0.0253 0.0225 9.15 1.165 0.0318 0.0341 0.0345 0.0293 0.0295 10.17 1.213 0.0394 0.0402 0.0449 0.0369 0.0355 Tabulated from data in file CL01112.DAT & reduced using program Q05.01D Average Reynolds #: 199800 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.23 -0.250 0.0256 0.0232 0.0273 0.0248 0.0271 -4.15 -0.125 0.0183 0.0175 0.0198 0.0188 0.0172 -3.13 0.016 0.0149 0.0138 0.0153 0.0151 0.0155 -2.10 0.135 0.0117 0.0111 0.0122 0.0117 0.0118 -1.07 0.231 0.0099 0.0085 0.0114 0.0104 0.0093 -0.03 0.332 0.0099 0.0088 0.0107 0.0102 0.0097 1.01 0.443 0.0102 0.0093 0.0103 0.0108 0.0104 2.01 0.548 0.0099 0.0088 0.0111 0.0107 0.0090 3.06 0.660 0.0103 0.0097 0.0103 0.0105 0.0107 4.08 0.762 0.0111 0.0110 0.0113 0.0108 0.0111 5.10 0.859 0.0124 0.0119 0.0127 0.0125 0.0126 6.12 0.949 0.0146 0.0139 0.0150 0.0150 0.0143 7.15 1.029 0.0186 0.0179 0.0193 0.0188 0.0186 8.24 1.108 0.0227 0.0222 0.0228 0.0226 0.0232 9.20 1.176 0.0266 0.0260 0.0276 0.0264 0.0264 10.19 1.224 0.0328 0.0310 0.0380 0.0327 0.0295 Tabulated from data in file CL01114.DAT & reduced using program Q05.01D Average Reynolds #: 299800 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -5.20 -0.204 0.0216 0.0209 0.0226 0.0209 0.0221 -4.16 -0.087 0.0146 0.0130 0.0163 0.0147 0.0144 -3.14 0.024 0.0118 0.0097 0.0135 0.0128 0.0111 -2.11 0.122 0.0107 0.0112 0.0096 0.0113 0.0106 -1.09 0.233 0.0086 0.0091 0.0079 0.0094 0.0081 -0.08 0.334 0.0077 0.0080 0.0067 0.0090 0.0069 0.98 0.455 0.0077 0.0076 0.0076 0.0077 0.0077 2.00 0.571 0.0082 0.0077 0.0084 0.0087 0.0080 3.08 0.681 0.0087 0.0083 0.0091 0.0087 0.0087 4.06 0.781 0.0096 0.0092 0.0098 0.0095 0.0100 5.08 0.883 0.0110 0.0105 0.0111 0.0110 0.0114 6.09 0.975 0.0132 0.0127 0.0133 0.0129 0.0137 7.14 1.060 0.0164 0.0158 0.0167 0.0161 0.0171 8.15 1.141 0.0197 0.0195 0.0200 0.0193 0.0200 9.23 1.219 0.0231 0.0219 0.0252 0.0234 0.0218 10.21 1.268 0.0292 0.0264 0.0347 0.0296 0.0260 Tabulated from data in file CL01116.DAT & reduced using program Q05.01D File S7075B0.DRG created on 09-12-1997 at 13:39:49 using program FORMAT