Airfoil: Ultra-Sport 1000 Builder: D. Brengman Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 101100 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -3.03 -0.307 0.0214 0.0191 0.0213 0.0181 0.0269 -1.97 -0.202 0.0205 0.0204 0.0201 0.0191 0.0223 -0.96 -0.125 0.0209 0.0205 0.0200 0.0205 0.0224 0.05 -0.032 0.0219 0.0206 0.0216 0.0219 0.0233 1.08 0.059 0.0213 0.0191 0.0223 0.0205 0.0234 2.09 0.142 0.0210 0.0197 0.0217 0.0207 0.0219 3.12 0.217 0.0214 0.0209 0.0207 0.0198 0.0241 4.14 0.308 0.0207 0.0203 0.0216 0.0185 0.0224 5.28 0.481 0.0237 0.0247 0.0242 0.0209 0.0250 6.18 0.594 0.0231 0.0259 0.0220 0.0215 0.0229 7.21 0.639 0.0253 0.0287 0.0231 0.0233 0.0260 8.23 0.713 0.0249 0.0269 0.0256 0.0232 0.0240 9.26 0.813 0.0242 0.0257 0.0211 0.0273 0.0227 10.28 0.881 0.0261 0.0265 0.0252 0.0256 0.0269 11.30 0.937 0.0331 0.0349 0.0286 0.0311 0.0376 Tabulated from data in file CL01680.DAT & reduced using program Q05.01D Average Reynolds #: 201500 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -3.02 -0.311 0.0149 0.0147 0.0135 0.0154 0.0159 -2.00 -0.215 0.0143 0.0146 0.0135 0.0145 0.0146 -1.00 -0.117 0.0137 0.0142 0.0131 0.0138 0.0139 0.05 -0.015 0.0135 0.0140 0.0128 0.0136 0.0137 1.07 0.080 0.0132 0.0136 0.0126 0.0132 0.0133 2.08 0.180 0.0139 0.0138 0.0134 0.0143 0.0139 3.11 0.278 0.0141 0.0139 0.0145 0.0145 0.0134 4.13 0.372 0.0151 0.0144 0.0155 0.0149 0.0155 5.17 0.464 0.0154 0.0140 0.0156 0.0154 0.0168 6.18 0.561 0.0160 0.0146 0.0163 0.0154 0.0175 7.22 0.693 0.0179 0.0167 0.0164 0.0167 0.0218 8.27 0.799 0.0169 0.0158 0.0155 0.0178 0.0184 9.29 0.868 0.0213 0.0197 0.0200 0.0213 0.0242 10.28 0.907 0.0281 0.0249 0.0242 0.0295 0.0336 11.27 0.914 0.0539 0.0273 0.0266 0.0730 0.0887 12.27 0.905 0.0691 0.0296 0.0305 0.0917 0.1245 Tabulated from data in file CL01682.DAT & reduced using program Q05.01D Average Reynolds #: 302100 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -3.04 -0.340 0.0127 0.0125 0.0127 0.0127 0.0129 -1.99 -0.230 0.0121 0.0121 0.0119 0.0121 0.0125 -0.97 -0.125 0.0117 0.0120 0.0113 0.0117 0.0118 0.03 -0.023 0.0114 0.0118 0.0111 0.0113 0.0115 1.09 0.086 0.0113 0.0115 0.0110 0.0114 0.0114 2.10 0.189 0.0116 0.0116 0.0115 0.0117 0.0115 3.13 0.296 0.0118 0.0117 0.0120 0.0121 0.0114 4.16 0.402 0.0123 0.0122 0.0121 0.0129 0.0118 5.19 0.505 0.0129 0.0126 0.0131 0.0133 0.0126 6.22 0.599 0.0136 0.0131 0.0138 0.0139 0.0134 7.23 0.693 0.0133 0.0133 0.0135 0.0129 0.0135 8.26 0.805 0.0165 0.0159 0.0145 0.0169 0.0187 9.28 0.866 0.0209 0.0186 0.0189 0.0223 0.0237 10.28 0.894 0.0316 0.0249 0.0236 0.0316 0.0465 11.30 0.900 0.0536 0.0266 0.0244 0.0642 0.0992 Tabulated from data in file CL01684.DAT & reduced using program Q05.01D Average Reynolds #: 403400 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -3.07 -0.353 0.0111 0.0109 0.0108 0.0112 0.0115 -1.95 -0.235 0.0107 0.0107 0.0104 0.0106 0.0111 -0.97 -0.128 0.0106 0.0108 0.0104 0.0103 0.0110 0.04 -0.023 0.0105 0.0107 0.0102 0.0102 0.0108 1.07 0.084 0.0104 0.0106 0.0101 0.0102 0.0106 2.09 0.191 0.0104 0.0106 0.0101 0.0102 0.0105 3.13 0.305 0.0106 0.0106 0.0102 0.0109 0.0107 4.16 0.410 0.0111 0.0112 0.0106 0.0115 0.0112 5.20 0.516 0.0117 0.0116 0.0112 0.0121 0.0118 6.24 0.619 0.0121 0.0120 0.0120 0.0121 0.0123 7.23 0.706 0.0130 0.0124 0.0126 0.0126 0.0145 8.27 0.794 0.0144 0.0142 0.0123 0.0148 0.0165 9.29 0.854 0.0205 0.0178 0.0193 0.0213 0.0237 10.28 0.878 0.0337 0.0221 0.0218 0.0344 0.0565 11.29 0.882 0.0525 0.0237 0.0221 0.0631 0.1012 Tabulated from data in file CL01686.DAT & reduced using program Q05.01D Average Reynolds #: 504100 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -3.15 -0.368 0.0103 0.0105 0.0100 0.0101 0.0108 -1.83 -0.221 0.0100 0.0101 0.0096 0.0097 0.0104 -0.67 -0.093 0.0099 0.0102 0.0096 0.0096 0.0104 0.26 0.007 0.0098 0.0099 0.0096 0.0097 0.0101 1.09 0.092 0.0099 0.0101 0.0096 0.0099 0.0101 2.09 0.197 0.0099 0.0101 0.0095 0.0100 0.0100 3.12 0.303 0.0099 0.0100 0.0095 0.0102 0.0099 4.16 0.411 0.0103 0.0104 0.0099 0.0107 0.0102 5.23 0.522 0.0108 0.0108 0.0102 0.0113 0.0110 6.24 0.633 0.0115 0.0113 0.0109 0.0117 0.0120 7.61 0.748 0.0136 0.0126 0.0125 0.0131 0.0160 8.42 0.804 0.0162 0.0146 0.0147 0.0165 0.0188 9.84 0.864 0.0256 0.0197 0.0203 0.0248 0.0375 10.28 0.872 0.0359 0.0199 0.0195 0.0409 0.0634 Tabulated from data in file CL01861.DAT & reduced using program Q05.01D File US1000.DRG created on 09-12-1997 at 13:39:50 using program FORMAT