Airfoil: Avistar Builder: B. Champine Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 100000 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -3.32 -0.067 0.0207 0.0191 0.0200 0.0210 0.0226 -2.33 0.037 0.0203 0.0211 0.0188 0.0202 0.0212 -1.30 0.183 0.0210 0.0217 0.0237 0.0195 0.0189 -0.24 0.387 0.0225 0.0209 0.0243 0.0198 0.0252 0.77 0.453 0.0217 0.0216 0.0203 0.0203 0.0247 1.78 0.527 0.0218 0.0219 0.0204 0.0200 0.0249 2.90 0.612 0.0223 0.0241 0.0200 0.0204 0.0248 3.81 0.683 0.0223 0.0231 0.0198 0.0209 0.0253 4.93 0.777 0.0227 0.0218 0.0214 0.0206 0.0269 5.88 0.850 0.0216 0.0219 0.0209 0.0203 0.0232 6.89 0.925 0.0210 0.0221 0.0194 0.0203 0.0221 7.91 0.970 0.0237 0.0258 0.0254 0.0208 0.0228 8.94 0.987 0.0315 0.0342 0.0353 0.0262 0.0303 9.90 1.008 0.0364 0.0397 0.0403 0.0313 0.0343 Tabulated from data in file CL01118.DAT & reduced using program Q05.01D Average Reynolds #: 200600 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -5.44 -0.210 0.0206 0.0195 0.0191 0.0205 0.0231 -4.32 -0.140 0.0174 0.0170 0.0161 0.0176 0.0187 -3.33 -0.047 0.0146 0.0142 0.0132 0.0148 0.0162 -2.29 0.032 0.0122 0.0119 0.0120 0.0121 0.0128 -1.33 0.130 0.0119 0.0123 0.0123 0.0115 0.0116 -0.25 0.245 0.0115 0.0102 0.0116 0.0121 0.0120 0.77 0.389 0.0124 0.0118 0.0114 0.0125 0.0141 1.78 0.523 0.0125 0.0118 0.0132 0.0124 0.0126 2.78 0.617 0.0130 0.0124 0.0135 0.0126 0.0136 3.82 0.726 0.0137 0.0134 0.0135 0.0135 0.0143 4.87 0.821 0.0145 0.0143 0.0138 0.0145 0.0153 5.90 0.888 0.0159 0.0160 0.0182 0.0149 0.0145 6.89 0.923 0.0203 0.0188 0.0247 0.0187 0.0189 7.89 0.950 0.0262 0.0258 0.0287 0.0251 0.0250 Tabulated from data in file CL01120.DAT & reduced using program Q05.01D Average Reynolds #: 300900 Number of angles of attack: 15 alpha / Cl / Cd / Spanwise Cd's >>> -5.37 -0.215 0.0173 0.0171 0.0171 0.0167 0.0185 -4.38 -0.154 0.0153 0.0152 0.0150 0.0147 0.0165 -3.32 -0.054 0.0134 0.0131 0.0127 0.0129 0.0150 -2.31 0.042 0.0105 0.0097 0.0098 0.0098 0.0126 -1.23 0.144 0.0095 0.0090 0.0095 0.0088 0.0107 -0.22 0.237 0.0098 0.0101 0.0102 0.0089 0.0100 0.78 0.416 0.0108 0.0109 0.0102 0.0111 0.0112 1.83 0.575 0.0112 0.0107 0.0100 0.0117 0.0125 2.85 0.679 0.0111 0.0105 0.0111 0.0110 0.0117 3.84 0.771 0.0116 0.0107 0.0117 0.0117 0.0122 4.86 0.853 0.0127 0.0107 0.0151 0.0112 0.0136 5.90 0.907 0.0169 0.0156 0.0196 0.0161 0.0164 6.93 0.944 0.0213 0.0204 0.0237 0.0205 0.0206 7.89 0.980 0.0257 0.0245 0.0287 0.0248 0.0246 8.91 1.011 0.0320 0.0308 0.0375 0.0306 0.0292 Tabulated from data in file CL01122.DAT & reduced using program Q05.01D Average Reynolds #: 402100 Number of angles of attack: 14 alpha / Cl / Cd / Spanwise Cd's >>> -5.42 -0.236 0.0158 0.0161 0.0156 0.0151 0.0164 -4.37 -0.144 0.0138 0.0140 0.0133 0.0133 0.0148 -3.35 -0.045 0.0122 0.0120 0.0117 0.0118 0.0134 -2.34 0.054 0.0100 0.0090 0.0097 0.0097 0.0117 -1.34 0.149 0.0084 0.0081 0.0087 0.0082 0.0088 -0.26 0.284 0.0087 0.0088 0.0084 0.0085 0.0089 0.77 0.408 0.0096 0.0109 0.0088 0.0096 0.0091 1.80 0.546 0.0100 0.0092 0.0091 0.0110 0.0106 2.85 0.686 0.0090 0.0089 0.0063 0.0129 0.0079 3.87 0.784 0.0109 0.0099 0.0122 0.0107 0.0109 4.95 0.850 0.0130 0.0130 0.0152 0.0120 0.0116 5.88 0.886 0.0163 0.0149 0.0196 0.0155 0.0153 6.87 0.923 0.0206 0.0196 0.0229 0.0199 0.0201 7.91 0.964 0.0255 0.0237 0.0302 0.0239 0.0242 Tabulated from data in file CL01124.DAT & reduced using program Q05.01D File AVISTAR.DRG created on 09-12-1997 at 13:39:49 using program FORMAT