Airfoil: W1011-30 f0 Builder: S. Cassidy Comment: Clean, Cf/C = 30%, Flap = 0° Number of Reynolds #'s: 3 Average Reynolds #: 100108.2 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -8.25 -0.767 0.0265 0.0274 0.0267 0.0274 0.0249 0.0264 0.0266 0.0277 0.0246 -7.20 -0.684 0.0216 0.0213 0.0220 0.0231 0.0198 0.0204 0.0234 0.0230 0.0197 -6.23 -0.604 0.0192 0.0193 0.0189 0.0216 0.0181 0.0180 0.0203 0.0200 0.0177 -5.20 -0.516 0.0168 0.0167 0.0165 0.0185 0.0159 0.0157 0.0180 0.0166 0.0164 -4.12 -0.424 0.0153 0.0151 0.0147 0.0167 0.0148 0.0144 0.0160 0.0155 0.0154 -3.09 -0.343 0.0140 0.0136 0.0143 0.0151 0.0130 0.0132 0.0158 0.0138 0.0130 -2.08 -0.250 0.0128 0.0129 0.0138 0.0149 0.0114 0.0113 0.0131 0.0134 0.0115 -1.06 -0.175 0.0121 0.0133 0.0119 0.0144 0.0096 0.0104 0.0133 0.0125 0.0115 -0.08 0.001 0.0107 0.0120 0.0102 0.0122 0.0096 0.0098 0.0103 0.0131 0.0086 0.90 0.124 0.0131 0.0152 0.0112 0.0141 0.0123 0.0111 0.0127 0.0129 0.0154 1.91 0.210 0.0137 0.0098 0.0181 0.0156 0.0098 0.0164 0.0117 0.0171 0.0111 2.91 0.309 0.0150 0.0145 0.0155 0.0178 0.0156 0.0130 0.0131 0.0160 0.0149 3.92 0.402 0.0171 0.0158 0.0189 0.0167 0.0191 0.0153 0.0152 0.0194 0.0165 4.97 0.496 0.0190 0.0180 0.0227 0.0173 0.0203 0.0173 0.0167 0.0220 0.0177 6.07 0.604 0.0225 0.0215 0.0246 0.0220 0.0237 0.0217 0.0219 0.0249 0.0198 7.14 0.696 0.0271 0.0269 0.0284 0.0269 0.0285 0.0253 0.0262 0.0297 0.0253 8.17 0.780 0.0302 0.0295 0.0304 0.0305 0.0318 0.0288 0.0299 0.0314 0.0296 9.15 0.850 0.0354 0.0348 0.0359 0.0375 0.0369 0.0338 0.0348 0.0350 0.0344 10.06 0.918 0.0422 0.0410 0.0420 0.0443 0.0440 0.0421 0.0410 0.0414 0.0416 Tabulated from data in file 07129sn_interp.dat & reduced using program C10.20 Average Reynolds #: 199881.6 Number of angles of attack: 20 alpha / Cl / Cd / Spanwise Cd's >>> -8.21 -0.800 0.0187 0.0198 0.0195 0.0184 0.0186 0.0178 0.0188 0.0182 0.0183 -7.34 -0.723 0.0167 0.0174 0.0167 0.0170 0.0160 0.0162 0.0166 0.0172 0.0167 -6.19 -0.619 0.0145 0.0145 0.0141 0.0155 0.0140 0.0142 0.0144 0.0149 0.0147 -5.15 -0.514 0.0130 0.0131 0.0124 0.0145 0.0126 0.0128 0.0131 0.0130 0.0128 -4.19 -0.417 0.0118 0.0119 0.0116 0.0133 0.0113 0.0116 0.0118 0.0115 0.0116 -3.13 -0.312 0.0105 0.0106 0.0107 0.0117 0.0101 0.0097 0.0104 0.0101 0.0104 -2.07 -0.186 0.0097 0.0096 0.0097 0.0109 0.0088 0.0086 0.0097 0.0108 0.0096 -1.18 -0.117 0.0087 0.0089 0.0088 0.0092 0.0082 0.0077 0.0087 0.0093 0.0087 -0.11 -0.000 0.0090 0.0094 0.0074 0.0107 0.0090 0.0086 0.0093 0.0100 0.0078 0.98 0.121 0.0092 0.0107 0.0069 0.0098 0.0088 0.0096 0.0091 0.0100 0.0085 2.05 0.234 0.0101 0.0116 0.0099 0.0102 0.0093 0.0102 0.0097 0.0097 0.0104 3.07 0.331 0.0116 0.0120 0.0115 0.0117 0.0119 0.0112 0.0111 0.0111 0.0120 4.01 0.424 0.0130 0.0135 0.0134 0.0126 0.0132 0.0129 0.0125 0.0128 0.0132 5.12 0.538 0.0148 0.0151 0.0154 0.0148 0.0151 0.0146 0.0143 0.0148 0.0147 6.12 0.632 0.0166 0.0161 0.0165 0.0173 0.0171 0.0165 0.0165 0.0167 0.0160 7.00 0.713 0.0184 0.0177 0.0176 0.0196 0.0196 0.0187 0.0185 0.0182 0.0177 8.20 0.809 0.0216 0.0210 0.0205 0.0230 0.0228 0.0225 0.0216 0.0204 0.0209 9.03 0.871 0.0244 0.0239 0.0239 0.0250 0.0242 0.0246 0.0255 0.0239 0.0240 10.16 0.943 0.0304 0.0301 0.0298 0.0329 0.0316 0.0294 0.0316 0.0292 0.0288 11.10 0.994 0.0365 0.0360 0.0363 0.0392 0.0377 0.0358 0.0378 0.0347 0.0347 Tabulated from data in file 07131sn_interp.dat & reduced using program C10.20 Average Reynolds #: 399951.9 Number of angles of attack: 21 alpha / Cl / Cd / Spanwise Cd's >>> -8.41 -0.824 0.0151 0.0153 0.0155 0.0158 0.0146 0.0141 0.0149 0.0156 0.0148 -7.22 -0.712 0.0129 0.0131 0.0128 0.0134 0.0122 0.0124 0.0128 0.0136 0.0128 -6.34 -0.627 0.0117 0.0117 0.0113 0.0125 0.0109 0.0116 0.0117 0.0122 0.0116 -5.14 -0.507 0.0102 0.0101 0.0100 0.0113 0.0096 0.0100 0.0102 0.0103 0.0100 -4.31 -0.421 0.0098 0.0099 0.0100 0.0111 0.0097 0.0093 0.0095 0.0096 0.0091 -3.10 -0.294 0.0088 0.0088 0.0090 0.0098 0.0089 0.0081 0.0086 0.0087 0.0085 -2.07 -0.179 0.0081 0.0080 0.0075 0.0087 0.0091 0.0072 0.0076 0.0083 0.0082 -1.28 -0.103 0.0080 0.0083 0.0072 0.0085 0.0085 0.0070 0.0076 0.0083 0.0082 -0.01 0.018 0.0074 0.0078 0.0070 0.0077 0.0075 0.0070 0.0073 0.0074 0.0078 0.80 0.096 0.0073 0.0078 0.0071 0.0075 0.0069 0.0071 0.0071 0.0073 0.0075 1.94 0.212 0.0079 0.0083 0.0078 0.0074 0.0077 0.0081 0.0078 0.0076 0.0083 3.02 0.322 0.0093 0.0094 0.0092 0.0095 0.0092 0.0094 0.0091 0.0087 0.0094 3.93 0.403 0.0100 0.0101 0.0102 0.0099 0.0101 0.0103 0.0098 0.0096 0.0100 4.98 0.503 0.0111 0.0111 0.0114 0.0109 0.0116 0.0114 0.0109 0.0107 0.0110 5.99 0.607 0.0123 0.0120 0.0124 0.0123 0.0131 0.0121 0.0123 0.0119 0.0120 7.17 0.725 0.0139 0.0133 0.0138 0.0148 0.0147 0.0134 0.0141 0.0136 0.0135 8.05 0.803 0.0154 0.0144 0.0148 0.0171 0.0163 0.0147 0.0162 0.0150 0.0147 9.23 0.903 0.0185 0.0177 0.0177 0.0204 0.0192 0.0180 0.0198 0.0174 0.0177 10.22 0.974 0.0224 0.0217 0.0211 0.0245 0.0235 0.0218 0.0238 0.0214 0.0215 11.13 1.033 0.0262 0.0250 0.0248 0.0283 0.0269 0.0261 0.0279 0.0253 0.0250 12.20 1.081 0.0335 0.0327 0.0325 0.0357 0.0349 0.0335 0.0352 0.0324 0.0313 Tabulated from data in file 07133sn_interp.dat & reduced using program C10.20 File w1011-30_f0_drag.dat created using program clcm dist V1.1 on 30-Mar-2012 09:46:54