Airfoil: SD7037 (B) Builder: D. Thompson Comment: clean: flap = 10 degs Number of Reynolds #'s: 6 Average Reynolds #: 59500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.82 -0.027 0.0289 0.0270 0.0285 0.0303 0.0298 -3.28 0.111 0.0242 0.0273 0.0230 0.0232 0.0234 -1.75 0.240 0.0228 0.0283 0.0208 0.0226 0.0196 -0.21 0.391 0.0281 0.0284 0.0288 0.0276 0.0277 1.32 0.576 0.0325 0.0317 0.0300 0.0407 0.0276 2.91 0.846 0.0318 0.0311 0.0336 0.0317 0.0309 5.14 1.071 0.0230 0.0239 0.0217 0.0220 0.0243 5.98 1.127 0.0272 0.0287 0.0261 0.0279 0.0259 7.50 1.201 0.0307 0.0313 0.0340 0.0297 0.0280 9.00 1.262 0.0424 0.0405 0.0409 0.0457 0.0424 10.51 1.323 0.0490 0.0447 0.0528 0.0486 0.0500 Tabulated from data in file CL00815.DAT & reduced using program Q02.00D Average Reynolds #: 99400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.77 0.181 0.0235 0.0236 0.0224 0.0226 0.0254 -2.22 0.301 0.0214 0.0188 0.0217 0.0214 0.0235 -0.70 0.444 0.0224 0.0215 0.0224 0.0241 0.0215 0.49 0.570 0.0262 0.0290 0.0240 0.0261 0.0257 2.41 0.908 0.0215 0.0204 0.0202 0.0234 0.0219 3.97 1.051 0.0187 0.0166 0.0186 0.0199 0.0196 5.47 1.167 0.0228 0.0210 0.0228 0.0246 0.0227 7.01 1.262 0.0271 0.0268 0.0264 0.0295 0.0255 8.52 1.314 0.0367 0.0339 0.0356 0.0395 0.0378 10.03 1.370 0.0445 0.0399 0.0429 0.0474 0.0476 11.27 1.397 0.0541 0.0444 0.0540 0.0593 0.0587 Tabulated from data in file AG00817.DAT & reduced using program Q02.00D Average Reynolds #: 198400 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.76 0.306 0.0155 0.0144 0.0158 0.0162 0.0156 -2.13 0.469 0.0148 0.0132 0.0150 0.0160 0.0148 -0.65 0.620 0.0154 0.0143 0.0150 0.0180 0.0145 0.88 0.779 0.0153 0.0149 0.0156 0.0154 0.0153 2.42 0.932 0.0131 0.0130 0.0135 0.0129 0.0130 3.96 1.062 0.0163 0.0164 0.0164 0.0163 0.0162 5.48 1.175 0.0198 0.0202 0.0196 0.0196 0.0199 6.98 1.260 0.0247 0.0254 0.0234 0.0246 0.0253 8.52 1.330 0.0302 0.0310 0.0292 0.0301 0.0305 10.00 1.393 0.0359 0.0369 0.0349 0.0360 0.0360 11.54 1.427 0.0443 0.0443 0.0435 0.0452 0.0443 Tabulated from data in file AG00819.DAT & reduced using program Q02.00D Average Reynolds #: 200800 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -5.82 0.114 0.0190 0.0183 0.0186 0.0196 0.0197 -4.70 0.215 0.0166 0.0156 0.0162 0.0173 0.0173 Tabulated from data in file CL00820.DAT & reduced using program Q02.00D Average Reynolds #: 298800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.78 0.106 0.0154 0.0152 0.0150 0.0163 0.0151 -4.26 0.247 0.0135 0.0133 0.0136 0.0134 0.0136 -2.72 0.427 0.0128 0.0127 0.0129 0.0127 0.0130 -1.17 0.578 0.0147 0.0154 0.0139 0.0142 0.0154 0.37 0.744 0.0117 0.0118 0.0118 0.0119 0.0113 1.89 0.877 0.0110 0.0111 0.0109 0.0108 0.0111 3.42 1.007 0.0139 0.0138 0.0138 0.0138 0.0142 4.96 1.125 0.0172 0.0170 0.0171 0.0173 0.0174 6.53 1.218 0.0215 0.0215 0.0209 0.0217 0.0220 8.00 1.294 0.0260 0.0265 0.0246 0.0262 0.0265 9.50 1.374 0.0299 0.0305 0.0287 0.0300 0.0302 Tabulated from data in file CL00822.DAT & reduced using program Q02.00D Average Reynolds #: 301400 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -7.84 -0.142 0.0648 0.0609 0.0611 0.0719 0.0654 -6.80 0.010 0.0200 0.0190 0.0189 0.0223 0.0195 Tabulated from data in file CL00823.DAT & reduced using program Q02.00D File 7037bf10.drg created on 09-12-1997 at 13:46:25 using program FORMAT