XFOIL Version 6.96 Calculated polar for: RAE 100 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.250 -0.9325 0.10362 0.10093 0.0020 1.0000 0.0169 -15.000 -0.9808 0.08873 0.08583 -0.0076 1.0000 0.0165 -14.750 -1.0242 0.07608 0.07295 -0.0161 1.0000 0.0160 -14.500 -1.0511 0.06730 0.06397 -0.0221 1.0000 0.0159 -14.250 -1.0710 0.06031 0.05680 -0.0269 1.0000 0.0160 -14.000 -1.0865 0.05451 0.05083 -0.0305 1.0000 0.0160 -13.750 -1.1010 0.04937 0.04549 -0.0333 1.0000 0.0160 -13.500 -1.1099 0.04548 0.04144 -0.0350 1.0000 0.0164 -13.250 -1.1179 0.04208 0.03786 -0.0358 1.0000 0.0164 -13.000 -1.1251 0.03912 0.03473 -0.0356 1.0000 0.0166 -12.750 -1.1302 0.03672 0.03215 -0.0345 1.0000 0.0169 -12.500 -1.1334 0.03468 0.02993 -0.0327 1.0000 0.0170 -12.250 -1.1337 0.03310 0.02818 -0.0302 1.0000 0.0173 -12.000 -1.1319 0.03170 0.02660 -0.0275 1.0000 0.0175 -11.750 -1.1293 0.02953 0.02423 -0.0251 1.0000 0.0178 -11.500 -1.1227 0.02747 0.02205 -0.0231 1.0000 0.0183 -11.250 -1.1098 0.02625 0.02076 -0.0216 1.0000 0.0188 -11.000 -1.0941 0.02531 0.01975 -0.0203 1.0000 0.0193 -10.750 -1.0778 0.02429 0.01864 -0.0190 1.0000 0.0199 -10.500 -1.0602 0.02339 0.01763 -0.0178 1.0000 0.0207 -10.250 -1.0410 0.02264 0.01677 -0.0167 1.0000 0.0215 -10.000 -1.0215 0.02185 0.01586 -0.0156 1.0000 0.0221 -9.750 -1.0075 0.02020 0.01412 -0.0139 1.0000 0.0231 -9.500 -0.9876 0.01943 0.01333 -0.0129 1.0000 0.0241 -9.250 -0.9668 0.01875 0.01260 -0.0119 1.0000 0.0252 -9.000 -0.9455 0.01810 0.01187 -0.0109 1.0000 0.0264 -8.750 -0.9227 0.01763 0.01131 -0.0101 1.0000 0.0273 -8.500 -0.9056 0.01642 0.01007 -0.0086 1.0000 0.0293 -8.250 -0.8833 0.01590 0.00953 -0.0077 1.0000 0.0311 -8.000 -0.8607 0.01540 0.00897 -0.0068 1.0000 0.0329 -7.750 -0.8399 0.01467 0.00817 -0.0056 1.0000 0.0349 -7.500 -0.8182 0.01408 0.00758 -0.0046 1.0000 0.0377 -7.250 -0.7948 0.01370 0.00717 -0.0037 1.0000 0.0406 -7.000 -0.7735 0.01307 0.00652 -0.0025 1.0000 0.0443 -6.750 -0.7506 0.01265 0.00610 -0.0016 1.0000 0.0485 -6.500 -0.7282 0.01217 0.00560 -0.0005 1.0000 0.0537 -6.250 -0.7052 0.01179 0.00523 0.0004 1.0000 0.0600 -6.000 -0.6828 0.01133 0.00482 0.0014 1.0000 0.0686 -5.750 -0.6601 0.01093 0.00446 0.0024 1.0000 0.0790 -5.500 -0.6374 0.01054 0.00413 0.0034 1.0000 0.0927 -5.250 -0.6148 0.01018 0.00384 0.0044 1.0000 0.1097 -5.000 -0.5924 0.00981 0.00357 0.0055 1.0000 0.1305 -4.750 -0.5700 0.00947 0.00333 0.0065 1.0000 0.1543 -4.500 -0.5478 0.00913 0.00311 0.0076 1.0000 0.1810 -4.250 -0.5258 0.00882 0.00293 0.0087 1.0000 0.2096 -4.000 -0.5039 0.00854 0.00277 0.0098 1.0000 0.2396 -3.750 -0.4822 0.00828 0.00264 0.0109 1.0000 0.2705 -3.500 -0.4535 0.00803 0.00252 0.0106 0.9984 0.3053 -3.250 -0.4136 0.00776 0.00242 0.0079 0.9937 0.3463 -3.000 -0.3757 0.00750 0.00230 0.0057 0.9877 0.3850 -2.750 -0.3357 0.00726 0.00221 0.0031 0.9827 0.4243 -2.500 -0.2992 0.00702 0.00211 0.0013 0.9745 0.4601 -2.250 -0.2608 0.00680 0.00202 -0.0009 0.9671 0.4954 -2.000 -0.2237 0.00660 0.00193 -0.0027 0.9564 0.5291 -1.750 -0.1887 0.00641 0.00185 -0.0040 0.9416 0.5614 -1.500 -0.1564 0.00626 0.00177 -0.0046 0.9212 0.5910 -1.250 -0.1270 0.00615 0.00170 -0.0045 0.8964 0.6198 -1.000 -0.1005 0.00608 0.00165 -0.0038 0.8681 0.6471 -0.750 -0.0750 0.00604 0.00161 -0.0029 0.8391 0.6744 -0.500 -0.0500 0.00602 0.00158 -0.0019 0.8103 0.7009 -0.250 -0.0250 0.00601 0.00156 -0.0010 0.7823 0.7275 0.000 0.0000 0.00602 0.00156 0.0000 0.7547 0.7547 0.250 0.0250 0.00601 0.00156 0.0010 0.7275 0.7824 0.500 0.0499 0.00602 0.00158 0.0019 0.7009 0.8103 0.750 0.0749 0.00604 0.00161 0.0029 0.6742 0.8391 1.000 0.1005 0.00608 0.00165 0.0038 0.6471 0.8681 1.250 0.1270 0.00615 0.00170 0.0045 0.6197 0.8964 1.500 0.1564 0.00626 0.00177 0.0046 0.5910 0.9212 1.750 0.1887 0.00641 0.00185 0.0039 0.5613 0.9416 2.000 0.2236 0.00660 0.00193 0.0027 0.5292 0.9563 2.250 0.2608 0.00680 0.00202 0.0009 0.4955 0.9669 2.500 0.2992 0.00703 0.00211 -0.0013 0.4600 0.9744 2.750 0.3357 0.00726 0.00221 -0.0031 0.4240 0.9826 3.000 0.3757 0.00750 0.00231 -0.0057 0.3849 0.9877 3.250 0.4137 0.00776 0.00242 -0.0079 0.3466 0.9936 3.500 0.4534 0.00803 0.00253 -0.0106 0.3054 0.9984 3.750 0.4824 0.00828 0.00264 -0.0110 0.2703 1.0000 4.000 0.5041 0.00854 0.00277 -0.0098 0.2395 1.0000 4.250 0.5261 0.00882 0.00293 -0.0087 0.2096 1.0000 4.500 0.5481 0.00913 0.00312 -0.0076 0.1811 1.0000 4.750 0.5702 0.00947 0.00333 -0.0066 0.1542 1.0000 5.000 0.5926 0.00981 0.00357 -0.0055 0.1303 1.0000 5.250 0.6150 0.01018 0.00384 -0.0045 0.1096 1.0000 5.500 0.6376 0.01055 0.00413 -0.0035 0.0927 1.0000 5.750 0.6603 0.01093 0.00446 -0.0025 0.0790 1.0000 6.000 0.6830 0.01133 0.00482 -0.0015 0.0685 1.0000 6.250 0.7053 0.01180 0.00524 -0.0004 0.0600 1.0000 6.500 0.7284 0.01217 0.00560 0.0005 0.0538 1.0000 6.750 0.7508 0.01265 0.00610 0.0016 0.0484 1.0000 7.000 0.7736 0.01307 0.00652 0.0025 0.0443 1.0000 7.250 0.7948 0.01370 0.00717 0.0037 0.0406 1.0000 7.500 0.8181 0.01409 0.00759 0.0046 0.0377 1.0000 7.750 0.8398 0.01468 0.00818 0.0056 0.0349 1.0000 8.000 0.8605 0.01541 0.00898 0.0068 0.0329 1.0000 8.250 0.8832 0.01590 0.00952 0.0077 0.0311 1.0000 8.500 0.9055 0.01641 0.01006 0.0086 0.0293 1.0000 8.750 0.9229 0.01758 0.01126 0.0100 0.0274 1.0000 9.000 0.9453 0.01809 0.01186 0.0109 0.0264 1.0000 9.250 0.9666 0.01875 0.01260 0.0119 0.0253 1.0000 9.500 0.9875 0.01942 0.01332 0.0129 0.0241 1.0000 9.750 1.0072 0.02020 0.01414 0.0140 0.0232 1.0000 10.000 1.0217 0.02176 0.01577 0.0156 0.0222 1.0000 10.250 1.0408 0.02260 0.01673 0.0167 0.0214 1.0000 10.500 1.0594 0.02345 0.01770 0.0179 0.0208 1.0000 10.750 1.0773 0.02429 0.01864 0.0191 0.0199 1.0000 11.000 1.0939 0.02522 0.01966 0.0204 0.0193 1.0000 11.250 1.1094 0.02620 0.02072 0.0217 0.0188 1.0000 11.500 1.1222 0.02747 0.02206 0.0233 0.0184 1.0000 11.750 1.1280 0.02960 0.02431 0.0253 0.0178 1.0000 12.000 1.1320 0.03147 0.02638 0.0276 0.0174 1.0000 12.250 1.1345 0.03280 0.02787 0.0303 0.0172 1.0000 12.500 1.1334 0.03458 0.02982 0.0327 0.0170 1.0000 12.750 1.1306 0.03657 0.03199 0.0346 0.0168 1.0000 13.000 1.1254 0.03901 0.03461 0.0357 0.0166 1.0000 13.250 1.1184 0.04194 0.03772 0.0358 0.0164 1.0000 13.500 1.1093 0.04549 0.04145 0.0350 0.0163 1.0000 13.750 1.1003 0.04943 0.04555 0.0333 0.0161 1.0000 14.000 1.0902 0.05392 0.05020 0.0308 0.0159 1.0000 14.250 1.0694 0.06054 0.05704 0.0267 0.0160 1.0000 14.500 1.0484 0.06778 0.06447 0.0218 0.0160 1.0000 14.750 1.0188 0.07712 0.07402 0.0154 0.0161 1.0000 15.000 0.9779 0.08940 0.08652 0.0071 0.0165 1.0000 15.250 0.9297 0.10440 0.10172 -0.0026 0.0169 1.0000