XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY RC-10(B)3 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.5400 0.09923 0.09553 -0.0164 1.0000 0.0245 -9.750 -0.5366 0.09603 0.09234 -0.0170 1.0000 0.0238 -9.250 -0.5740 0.07567 0.07201 -0.0336 1.0000 0.0198 -9.000 -0.5825 0.07139 0.06770 -0.0350 1.0000 0.0196 -8.750 -0.5913 0.06733 0.06359 -0.0351 1.0000 0.0195 -8.500 -0.5976 0.06292 0.05908 -0.0352 1.0000 0.0193 -8.250 -0.6030 0.05843 0.05447 -0.0344 1.0000 0.0192 -8.000 -0.6086 0.05400 0.04987 -0.0327 1.0000 0.0191 -7.750 -0.6161 0.05000 0.04569 -0.0295 1.0000 0.0189 -7.500 -0.6261 0.04638 0.04186 -0.0249 1.0000 0.0188 -7.250 -0.6185 0.04069 0.03572 -0.0241 0.9945 0.0188 -7.000 -0.6051 0.03500 0.02938 -0.0235 0.9876 0.0192 -6.750 -0.5862 0.03070 0.02433 -0.0229 0.9822 0.0197 -6.500 -0.5632 0.02788 0.02102 -0.0227 0.9769 0.0199 -6.250 -0.5362 0.02550 0.01829 -0.0232 0.9733 0.0201 -6.000 -0.5107 0.02376 0.01628 -0.0231 0.9678 0.0204 -5.750 -0.4821 0.02230 0.01461 -0.0235 0.9633 0.0207 -5.500 -0.4514 0.02101 0.01313 -0.0243 0.9599 0.0212 -5.250 -0.4241 0.01993 0.01188 -0.0243 0.9544 0.0218 -5.000 -0.3952 0.01891 0.01073 -0.0246 0.9495 0.0224 -4.750 -0.3650 0.01798 0.00968 -0.0251 0.9456 0.0232 -4.500 -0.3385 0.01733 0.00892 -0.0248 0.9395 0.0246 -4.250 -0.3118 0.01657 0.00812 -0.0247 0.9339 0.0260 -4.000 -0.2848 0.01596 0.00750 -0.0245 0.9291 0.0272 -3.750 -0.2606 0.01542 0.00693 -0.0237 0.9219 0.0286 -3.500 -0.2344 0.01491 0.00636 -0.0233 0.9167 0.0303 -3.250 -0.2107 0.01444 0.00585 -0.0224 0.9098 0.0326 -3.000 -0.1855 0.01405 0.00545 -0.0218 0.9036 0.0368 -2.750 -0.1607 0.01366 0.00509 -0.0211 0.8978 0.0449 -2.500 -0.1364 0.01330 0.00475 -0.0202 0.8908 0.0592 -2.250 -0.1115 0.01292 0.00447 -0.0195 0.8854 0.0845 -2.000 -0.0884 0.01253 0.00428 -0.0187 0.8778 0.1292 -1.750 -0.0672 0.01185 0.00405 -0.0175 0.8714 0.2362 -1.500 -0.0569 0.01053 0.00381 -0.0143 0.8632 0.5081 -1.250 0.0220 0.00996 0.00457 -0.0234 0.8632 0.8985 -1.000 0.0540 0.01033 0.00484 -0.0233 0.8566 0.9342 -0.750 0.0974 0.01075 0.00518 -0.0258 0.8504 0.9603 -0.500 0.1660 0.01103 0.00535 -0.0339 0.8442 0.9835 -0.250 0.2121 0.01092 0.00514 -0.0377 0.8356 0.9915 0.000 0.2439 0.01083 0.00498 -0.0386 0.8254 0.9948 0.250 0.2773 0.01071 0.00480 -0.0398 0.8148 0.9971 0.500 0.3094 0.01061 0.00464 -0.0408 0.8043 0.9996 0.750 0.3351 0.01055 0.00451 -0.0403 0.7925 1.0000 1.000 0.3599 0.01050 0.00442 -0.0397 0.7791 1.0000 1.250 0.3847 0.01046 0.00433 -0.0391 0.7653 1.0000 1.500 0.4097 0.01044 0.00427 -0.0385 0.7514 1.0000 1.750 0.4347 0.01042 0.00422 -0.0379 0.7367 1.0000 2.000 0.4596 0.01042 0.00416 -0.0373 0.7198 1.0000 2.250 0.4844 0.01043 0.00411 -0.0366 0.6990 1.0000 2.500 0.5092 0.01047 0.00409 -0.0359 0.6755 1.0000 2.750 0.5340 0.01053 0.00408 -0.0353 0.6524 1.0000 3.000 0.5587 0.01062 0.00409 -0.0346 0.6254 1.0000 3.250 0.5830 0.01076 0.00411 -0.0339 0.5888 1.0000 3.500 0.6067 0.01099 0.00416 -0.0330 0.5442 1.0000 3.750 0.6299 0.01131 0.00425 -0.0322 0.4947 1.0000 4.000 0.6521 0.01174 0.00441 -0.0314 0.4376 1.0000 4.250 0.6740 0.01223 0.00464 -0.0305 0.3818 1.0000 4.500 0.6958 0.01270 0.00489 -0.0296 0.3339 1.0000 4.750 0.7173 0.01318 0.00516 -0.0288 0.2892 1.0000 5.250 0.7597 0.01414 0.00581 -0.0269 0.2128 1.0000 5.500 0.7802 0.01465 0.00616 -0.0258 0.1776 1.0000 5.750 0.8001 0.01521 0.00656 -0.0247 0.1452 1.0000 6.000 0.8199 0.01575 0.00700 -0.0235 0.1182 1.0000 6.250 0.8392 0.01632 0.00746 -0.0222 0.0970 1.0000 6.500 0.8583 0.01688 0.00796 -0.0208 0.0813 1.0000 6.750 0.8771 0.01744 0.00849 -0.0194 0.0704 1.0000 7.000 0.8951 0.01805 0.00907 -0.0178 0.0628 1.0000 7.250 0.9137 0.01856 0.00965 -0.0163 0.0579 1.0000 7.500 0.9308 0.01918 0.01027 -0.0146 0.0534 1.0000 7.750 0.9475 0.01981 0.01094 -0.0128 0.0500 1.0000 8.000 0.9643 0.02039 0.01160 -0.0110 0.0472 1.0000 8.250 0.9800 0.02104 0.01232 -0.0091 0.0449 1.0000 8.500 0.9934 0.02186 0.01314 -0.0069 0.0428 1.0000 8.750 1.0074 0.02260 0.01396 -0.0047 0.0411 1.0000 9.000 1.0220 0.02328 0.01473 -0.0026 0.0393 1.0000 9.250 1.0357 0.02399 0.01554 -0.0004 0.0377 1.0000 9.500 1.0483 0.02477 0.01638 0.0019 0.0364 1.0000 9.750 1.0597 0.02563 0.01728 0.0043 0.0352 1.0000 10.000 1.0689 0.02672 0.01840 0.0069 0.0341 1.0000 10.250 1.0798 0.02772 0.01949 0.0094 0.0332 1.0000 10.500 1.0903 0.02858 0.02050 0.0119 0.0321 1.0000 10.750 1.0985 0.02947 0.02152 0.0147 0.0311 1.0000 11.000 1.1060 0.03042 0.02257 0.0175 0.0301 1.0000 11.250 1.1135 0.03146 0.02371 0.0201 0.0293 1.0000 11.500 1.1210 0.03258 0.02492 0.0225 0.0286 1.0000 11.750 1.1283 0.03379 0.02621 0.0247 0.0279 1.0000 12.000 1.1350 0.03522 0.02770 0.0268 0.0273 1.0000 12.250 1.1410 0.03695 0.02954 0.0287 0.0266 1.0000 12.500 1.1459 0.03848 0.03131 0.0306 0.0259 1.0000 12.750 1.1494 0.04021 0.03326 0.0324 0.0252 1.0000 13.000 1.1516 0.04213 0.03538 0.0341 0.0246 1.0000 13.250 1.1523 0.04426 0.03771 0.0355 0.0241 1.0000 13.500 1.1516 0.04657 0.04019 0.0367 0.0236 1.0000 13.750 1.1498 0.04902 0.04282 0.0376 0.0231 1.0000 14.000 1.1473 0.05162 0.04557 0.0381 0.0227 1.0000 14.250 1.1442 0.05438 0.04846 0.0383 0.0224 1.0000 14.500 1.1403 0.05735 0.05155 0.0382 0.0220 1.0000 14.750 1.1354 0.06062 0.05493 0.0378 0.0217 1.0000 15.000 1.1279 0.06441 0.05885 0.0370 0.0214 1.0000 15.250 1.1156 0.06909 0.06369 0.0355 0.0212 1.0000 15.500 1.0985 0.07485 0.06969 0.0330 0.0210 1.0000 15.750 1.0791 0.08151 0.07658 0.0296 0.0209 1.0000 16.000 1.0572 0.08917 0.08445 0.0253 0.0209 1.0000 16.250 1.0326 0.09794 0.09342 0.0201 0.0209 1.0000 16.500 1.0045 0.10805 0.10371 0.0140 0.0210 1.0000 16.750 0.9713 0.11996 0.11579 0.0069 0.0212 1.0000