Airfoil: sg6050 Builder: M. Fox Comment: clean Number of Reynolds #'s: 12 Average Reynolds #: 398166 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -6.01 -0.247 0.0132 0.0132 0.0134 0.0123 0.0137 -4.94 -0.153 0.0116 0.0123 0.0117 0.0109 0.0116 Tabulated from data in file pg02758.dat & reduced using program C07.02 Average Reynolds #: 399285 Number of angles of attack: 20 alpha / Cl / Cd / Spanwise Cd's >>> -7.01 -0.340 0.0145 0.0142 0.0157 0.0139 0.0143 -6.00 -0.248 0.0132 0.0134 0.0136 0.0124 0.0136 -4.90 -0.149 0.0115 0.0122 0.0116 0.0108 0.0114 -3.90 -0.049 0.0110 0.0116 0.0114 0.0099 0.0110 -2.84 0.055 0.0112 0.0116 0.0116 0.0105 0.0111 -1.82 0.157 0.0111 0.0114 0.0112 0.0106 0.0113 -0.80 0.256 0.0110 0.0111 0.0107 0.0108 0.0115 0.21 0.364 0.0109 0.0110 0.0104 0.0109 0.0112 1.25 0.468 0.0103 0.0105 0.0099 0.0103 0.0106 2.25 0.567 0.0094 0.0095 0.0086 0.0096 0.0100 3.27 0.695 0.0092 0.0089 0.0083 0.0083 0.0113 4.35 0.815 0.0102 0.0098 0.0100 0.0108 0.0102 5.37 0.911 0.0106 0.0100 0.0107 0.0110 0.0106 6.39 1.008 0.0112 0.0109 0.0114 0.0113 0.0113 7.41 1.099 0.0122 0.0124 0.0122 0.0121 0.0122 8.41 1.190 0.0134 0.0140 0.0132 0.0133 0.0134 9.47 1.273 0.0151 0.0156 0.0146 0.0150 0.0153 10.50 1.333 0.0170 0.0177 0.0165 0.0167 0.0173 11.47 1.355 0.0205 0.0217 0.0199 0.0202 0.0201 12.49 1.363 0.0267 0.0352 0.0243 0.0247 0.0227 Tabulated from data in file pg02759.dat & reduced using program C07.02 Average Reynolds #: 397493 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -8.01 -0.428 0.0159 0.0154 0.0172 0.0156 0.0155 Tabulated from data in file pg02760.dat & reduced using program C07.02 Average Reynolds #: 399265 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -9.03 -0.512 0.0179 0.0174 0.0196 0.0177 0.0171 Tabulated from data in file pg02761.dat & reduced using program C07.02 Average Reynolds #: 498942 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -9.05 -0.553 0.0165 0.0162 0.0180 0.0161 0.0159 -8.06 -0.469 0.0146 0.0142 0.0156 0.0146 0.0142 -7.05 -0.380 0.0134 0.0129 0.0142 0.0130 0.0134 -6.05 -0.278 0.0123 0.0120 0.0125 0.0121 0.0126 -4.98 -0.179 0.0110 0.0112 0.0108 0.0108 0.0110 -3.94 -0.075 0.0102 0.0107 0.0101 0.0097 0.0101 -2.91 0.025 0.0101 0.0105 0.0102 0.0096 0.0100 -1.78 0.139 0.0103 0.0105 0.0103 0.0100 0.0104 -0.77 0.234 0.0103 0.0102 0.0100 0.0102 0.0105 0.19 0.334 0.0101 0.0101 0.0093 0.0104 0.0104 Tabulated from data in file pg02763.dat & reduced using program C07.02 Average Reynolds #: 500165 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -0.77 0.241 0.0103 0.0104 0.0101 0.0102 0.0104 0.21 0.342 0.0100 0.0099 0.0093 0.0104 0.0102 1.23 0.446 0.0097 0.0097 0.0090 0.0103 0.0098 2.29 0.555 0.0093 0.0094 0.0088 0.0096 0.0092 3.29 0.673 0.0086 0.0087 0.0078 0.0083 0.0094 4.28 0.790 0.0091 0.0095 0.0087 0.0089 0.0094 5.34 0.897 0.0101 0.0098 0.0100 0.0106 0.0098 6.34 0.988 0.0108 0.0106 0.0108 0.0112 0.0106 7.42 1.092 0.0116 0.0115 0.0116 0.0117 0.0115 8.47 1.178 0.0129 0.0131 0.0125 0.0130 0.0130 9.43 1.247 0.0143 0.0148 0.0138 0.0143 0.0145 10.43 1.299 0.0165 0.0169 0.0162 0.0164 0.0165 11.60 1.323 0.0214 0.0247 0.0209 0.0198 0.0203 12.50 1.329 0.0283 0.0363 0.0285 0.0224 0.0259 Tabulated from data in file pg02764.dat & reduced using program C07.02 Average Reynolds #: 299962 Number of angles of attack: 20 alpha / Cl / Cd / Spanwise Cd's >>> -9.04 -0.509 0.0204 0.0194 0.0214 0.0208 0.0199 -7.98 -0.418 0.0177 0.0172 0.0184 0.0175 0.0176 -6.97 -0.336 0.0160 0.0162 0.0167 0.0153 0.0160 -6.00 -0.251 0.0146 0.0151 0.0143 0.0135 0.0155 -4.93 -0.159 0.0129 0.0141 0.0128 0.0122 0.0126 -3.88 -0.056 0.0128 0.0136 0.0127 0.0119 0.0129 -2.86 0.048 0.0126 0.0133 0.0125 0.0119 0.0126 -1.85 0.153 0.0126 0.0130 0.0122 0.0121 0.0130 -0.83 0.254 0.0124 0.0129 0.0120 0.0119 0.0128 0.19 0.361 0.0119 0.0122 0.0115 0.0120 0.0121 1.24 0.459 0.0112 0.0114 0.0108 0.0113 0.0114 2.24 0.577 0.0108 0.0106 0.0095 0.0102 0.0129 3.27 0.703 0.0111 0.0109 0.0106 0.0114 0.0116 4.33 0.803 0.0116 0.0111 0.0114 0.0120 0.0116 5.34 0.898 0.0119 0.0112 0.0120 0.0125 0.0119 6.36 0.995 0.0125 0.0121 0.0128 0.0127 0.0124 7.36 1.083 0.0135 0.0137 0.0136 0.0134 0.0134 8.40 1.178 0.0145 0.0151 0.0143 0.0142 0.0142 9.46 1.267 0.0161 0.0166 0.0156 0.0158 0.0162 10.45 1.333 0.0178 0.0182 0.0173 0.0176 0.0182 Tabulated from data in file pg02766.dat & reduced using program C07.02 Average Reynolds #: 299740 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 11.40 1.365 0.0204 0.0212 0.0197 0.0205 0.0202 12.48 1.374 0.0258 0.0303 0.0248 0.0252 0.0231 Tabulated from data in file pg02767.dat & reduced using program C07.02 Average Reynolds #: 200121 Number of angles of attack: 22 alpha / Cl / Cd / Spanwise Cd's >>> -8.99 -0.509 0.0254 0.0240 0.0259 0.0265 0.0251 -7.97 -0.396 0.0220 0.0216 0.0209 0.0235 0.0221 -6.97 -0.312 0.0195 0.0206 0.0183 0.0198 0.0195 -5.98 -0.232 0.0170 0.0177 0.0156 0.0171 0.0176 -4.90 -0.144 0.0164 0.0174 0.0153 0.0165 0.0166 -3.83 -0.040 0.0163 0.0170 0.0154 0.0158 0.0167 -2.83 0.054 0.0160 0.0170 0.0155 0.0153 0.0164 -1.80 0.153 0.0157 0.0166 0.0157 0.0143 0.0162 -0.79 0.249 0.0149 0.0158 0.0141 0.0142 0.0156 0.19 0.347 0.0143 0.0149 0.0140 0.0137 0.0148 1.23 0.466 0.0139 0.0137 0.0125 0.0123 0.0171 2.29 0.602 0.0145 0.0141 0.0146 0.0142 0.0151 3.26 0.690 0.0146 0.0142 0.0151 0.0147 0.0145 4.32 0.789 0.0149 0.0143 0.0153 0.0152 0.0148 5.34 0.883 0.0153 0.0149 0.0157 0.0155 0.0153 6.35 0.977 0.0160 0.0159 0.0162 0.0161 0.0158 7.36 1.067 0.0167 0.0170 0.0168 0.0168 0.0163 8.40 1.162 0.0177 0.0185 0.0173 0.0177 0.0172 9.43 1.244 0.0191 0.0196 0.0185 0.0191 0.0191 10.42 1.320 0.0207 0.0210 0.0197 0.0212 0.0208 11.42 1.374 0.0227 0.0231 0.0217 0.0236 0.0223 12.45 1.374 0.0260 0.0267 0.0249 0.0269 0.0254 Tabulated from data in file pg02769.dat & reduced using program C07.02 Average Reynolds #: 149864 Number of angles of attack: 21 alpha / Cl / Cd / Spanwise Cd's >>> -7.94 -0.431 0.0261 0.0250 0.0247 0.0270 0.0278 -6.98 -0.318 0.0232 0.0223 0.0224 0.0225 0.0254 -5.97 -0.227 0.0203 0.0208 0.0185 0.0197 0.0219 -4.90 -0.134 0.0201 0.0213 0.0184 0.0202 0.0203 -3.86 -0.037 0.0199 0.0209 0.0186 0.0198 0.0204 -2.88 0.049 0.0193 0.0199 0.0187 0.0184 0.0201 -1.82 0.145 0.0191 0.0201 0.0192 0.0177 0.0192 -0.78 0.236 0.0187 0.0199 0.0182 0.0178 0.0190 0.18 0.326 0.0185 0.0196 0.0184 0.0170 0.0192 1.20 0.463 0.0186 0.0190 0.0176 0.0177 0.0201 2.25 0.565 0.0190 0.0193 0.0195 0.0182 0.0189 3.25 0.654 0.0188 0.0192 0.0194 0.0180 0.0186 4.33 0.756 0.0187 0.0187 0.0192 0.0181 0.0187 5.31 0.851 0.0190 0.0191 0.0185 0.0189 0.0196 6.35 0.948 0.0198 0.0204 0.0193 0.0194 0.0203 7.33 1.036 0.0206 0.0211 0.0202 0.0202 0.0209 8.41 1.135 0.0215 0.0223 0.0206 0.0212 0.0217 9.40 1.212 0.0225 0.0235 0.0210 0.0229 0.0227 10.42 1.284 0.0239 0.0242 0.0227 0.0249 0.0240 11.42 1.349 0.0252 0.0252 0.0244 0.0259 0.0251 12.44 1.375 0.0276 0.0284 0.0254 0.0288 0.0278 Tabulated from data in file rr02771.dat & reduced using program C07.02 Average Reynolds #: 99965 Number of angles of attack: 21 alpha / Cl / Cd / Spanwise Cd's >>> -7.94 -0.259 0.0347 0.0353 0.0357 0.0342 0.0335 -6.94 -0.235 0.0302 0.0321 0.0273 0.0324 0.0292 -6.00 -0.234 0.0283 0.0261 0.0265 0.0326 0.0280 -4.96 -0.226 0.0263 0.0257 0.0243 0.0251 0.0299 -3.94 -0.174 0.0268 0.0276 0.0249 0.0255 0.0293 -2.91 -0.069 0.0283 0.0288 0.0299 0.0270 0.0277 -1.87 0.014 0.0295 0.0273 0.0314 0.0295 0.0300 -0.83 0.086 0.0315 0.0299 0.0303 0.0325 0.0334 0.19 0.213 0.0329 0.0336 0.0321 0.0324 0.0337 1.15 0.276 0.0368 0.0355 0.0367 0.0368 0.0381 2.19 0.344 0.0369 0.0372 0.0377 0.0374 0.0354 3.19 0.420 0.0344 0.0363 0.0355 0.0338 0.0321 4.24 0.584 0.0324 0.0331 0.0324 0.0319 0.0323 5.29 0.752 0.0315 0.0326 0.0308 0.0312 0.0313 6.34 0.868 0.0293 0.0313 0.0280 0.0273 0.0305 7.33 0.963 0.0280 0.0301 0.0245 0.0270 0.0302 8.36 1.063 0.0285 0.0298 0.0244 0.0283 0.0313 9.38 1.153 0.0279 0.0270 0.0266 0.0285 0.0295 10.39 1.224 0.0297 0.0302 0.0268 0.0304 0.0312 11.39 1.288 0.0310 0.0301 0.0295 0.0325 0.0319 12.42 1.347 0.0322 0.0358 0.0298 0.0326 0.0305 Tabulated from data in file rr02773.dat & reduced using program C07.02 Average Reynolds #: 100025 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 13.45 1.347 0.0358 0.0351 0.0351 0.0379 0.0350 14.43 1.330 0.0448 0.0380 0.0470 0.0509 0.0434 Tabulated from data in file nr02774.dat & reduced using program C07.02 File sg6050a.drg created using program C07.02 on Wed May 20 23:12:03 1998