Airfoil: E472 Builder: D. Stanley Comment: clean Number of Reynolds #'s: 8 Average Reynolds #: 100300 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -2.95 -0.301 0.0177 0.0192 0.0169 0.0177 0.0171 -1.94 -0.209 0.0168 0.0182 0.0165 0.0166 0.0160 -0.90 -0.119 0.0141 0.0170 0.0141 0.0118 0.0133 0.16 0.047 0.0122 0.0158 0.0130 0.0099 0.0102 1.16 0.184 0.0146 0.0151 0.0160 0.0126 0.0147 2.21 0.278 0.0166 0.0172 0.0175 0.0166 0.0150 3.22 0.374 0.0187 0.0195 0.0187 0.0188 0.0177 4.24 0.465 0.0207 0.0217 0.0214 0.0207 0.0188 5.29 0.558 0.0240 0.0254 0.0238 0.0240 0.0229 6.28 0.639 0.0313 0.0317 0.0324 0.0305 0.0306 7.33 0.733 0.0380 0.0399 0.0400 0.0349 0.0371 8.34 0.730 0.1006 0.1210 0.1187 0.0954 0.0673 9.30 0.687 0.1452 0.1588 0.1559 0.1398 0.1264 10.32 0.667 0.1640 0.1653 0.1638 0.1700 0.1570 Tabulated from data in file CL01074.DAT & reduced using program Q05.01D Average Reynolds #: 200100 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -2.94 -0.335 0.0138 0.0145 0.0133 0.0132 0.0144 -1.90 -0.198 0.0130 0.0113 0.0140 0.0095 0.0170 -0.90 -0.064 0.0109 0.0106 0.0104 0.0096 0.0131 0.14 0.032 0.0102 0.0106 0.0103 0.0101 0.0100 1.15 0.118 0.0117 0.0107 0.0102 0.0159 0.0100 2.20 0.257 0.0132 0.0126 0.0114 0.0143 0.0146 3.22 0.367 0.0143 0.0140 0.0145 0.0148 0.0140 4.26 0.466 0.0156 0.0156 0.0155 0.0159 0.0155 5.27 0.561 0.0176 0.0180 0.0178 0.0176 0.0169 6.27 0.656 0.0196 0.0196 0.0202 0.0194 0.0193 7.31 0.748 0.0221 0.0218 0.0229 0.0217 0.0220 8.35 0.842 0.0245 0.0240 0.0256 0.0238 0.0247 9.35 0.929 0.0273 0.0264 0.0282 0.0268 0.0279 10.40 1.013 0.0307 0.0296 0.0321 0.0296 0.0314 11.42 1.084 0.0345 0.0327 0.0360 0.0345 0.0347 Tabulated from data in file CL01076.DAT & reduced using program Q05.01D Average Reynolds #: 200100 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> 12.26 0.671 0.1673 0.1751 0.1729 0.1555 0.1659 Tabulated from data in file CL01857.DAT & reduced using program Q05.01D Average Reynolds #: 300900 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -2.89 -0.333 0.0120 0.0128 0.0122 0.0112 0.0118 -1.88 -0.179 0.0112 0.0115 0.0113 0.0104 0.0117 -0.85 -0.058 0.0103 0.0106 0.0102 0.0100 0.0103 0.21 0.036 0.0106 0.0110 0.0107 0.0103 0.0106 1.15 0.121 0.0102 0.0106 0.0103 0.0098 0.0101 2.19 0.247 0.0109 0.0104 0.0100 0.0118 0.0113 3.24 0.384 0.0121 0.0119 0.0121 0.0122 0.0121 4.33 0.486 0.0131 0.0130 0.0131 0.0135 0.0129 5.26 0.573 0.0143 0.0141 0.0145 0.0145 0.0141 6.29 0.669 0.0155 0.0152 0.0160 0.0154 0.0155 7.34 0.769 0.0169 0.0165 0.0173 0.0169 0.0170 8.37 0.867 0.0181 0.0176 0.0184 0.0179 0.0186 9.47 0.969 0.0198 0.0194 0.0202 0.0193 0.0205 10.58 1.067 0.0224 0.0213 0.0234 0.0217 0.0234 11.44 1.135 0.0254 0.0240 0.0267 0.0252 0.0258 12.47 1.202 0.0294 0.0280 0.0307 0.0300 0.0290 Tabulated from data in file CL01078.DAT & reduced using program Q05.01D Average Reynolds #: 298100 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 13.71 1.245 0.0339 0.0311 0.0357 0.0356 0.0333 14.42 1.257 0.0409 0.0363 0.0437 0.0454 0.0384 Tabulated from data in file CL01858.DAT & reduced using program Q05.01D Average Reynolds #: 401000 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -2.90 -0.304 0.0105 0.0103 0.0115 0.0113 0.0089 -2.02 -0.185 0.0098 0.0099 0.0099 0.0095 0.0100 -0.81 -0.059 0.0101 0.0104 0.0101 0.0097 0.0102 0.18 0.036 0.0104 0.0106 0.0103 0.0101 0.0105 1.15 0.133 0.0102 0.0106 0.0102 0.0098 0.0101 2.19 0.234 0.0098 0.0099 0.0095 0.0099 0.0100 3.25 0.372 0.0105 0.0104 0.0093 0.0112 0.0111 4.25 0.484 0.0115 0.0115 0.0117 0.0115 0.0113 5.28 0.582 0.0125 0.0124 0.0127 0.0124 0.0124 6.38 0.690 0.0137 0.0134 0.0139 0.0139 0.0137 7.35 0.787 0.0146 0.0141 0.0149 0.0146 0.0147 8.45 0.894 0.0159 0.0153 0.0161 0.0157 0.0165 9.84 1.020 0.0179 0.0172 0.0181 0.0177 0.0186 10.45 1.063 0.0190 0.0183 0.0193 0.0187 0.0198 11.64 1.156 0.0225 0.0213 0.0230 0.0227 0.0227 12.94 1.237 0.0277 0.0260 0.0288 0.0284 0.0274 Tabulated from data in file CL01080.DAT & reduced using program Q05.01D Average Reynolds #: 397000 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 13.90 1.271 0.0313 0.0288 0.0324 0.0332 0.0308 14.71 1.257 0.0732 0.0298 0.0568 0.1129 0.0933 Tabulated from data in file CL01859.DAT & reduced using program Q05.01D Average Reynolds #: 501400 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -3.14 -0.369 0.0099 0.0090 0.0115 0.0104 0.0087 -1.79 -0.192 0.0093 0.0094 0.0092 0.0090 0.0096 -0.48 -0.064 0.0098 0.0100 0.0098 0.0096 0.0100 0.45 0.028 0.0101 0.0102 0.0099 0.0100 0.0103 1.28 0.109 0.0102 0.0104 0.0100 0.0102 0.0103 2.28 0.210 0.0099 0.0101 0.0098 0.0096 0.0100 3.27 0.312 0.0094 0.0095 0.0088 0.0093 0.0101 4.20 0.433 0.0102 0.0109 0.0096 0.0102 0.0104 5.31 0.552 0.0112 0.0113 0.0112 0.0113 0.0110 6.24 0.635 0.0121 0.0119 0.0121 0.0123 0.0121 7.40 0.750 0.0131 0.0125 0.0132 0.0134 0.0132 8.40 0.850 0.0140 0.0135 0.0144 0.0140 0.0143 9.73 0.985 0.0156 0.0150 0.0159 0.0154 0.0161 10.74 1.079 0.0172 0.0168 0.0175 0.0168 0.0178 12.02 1.186 0.0207 0.0199 0.0208 0.0210 0.0212 12.40 1.209 0.0217 0.0206 0.0222 0.0218 0.0221 13.62 1.285 0.0276 0.0259 0.0283 0.0287 0.0273 Tabulated from data in file CL01856.DAT & reduced using program Q05.01D File E472.DRG created on 09-12-1997 at 13:39:49 using program FORMAT