XFOIL Version 6.96 Calculated polar for: RAF 34 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.500 -0.9763 0.06744 0.06444 -0.0409 1.0000 0.0162 -15.250 -1.0387 0.05217 0.04876 -0.0525 1.0000 0.0160 -15.000 -1.0396 0.04869 0.04519 -0.0548 1.0000 0.0163 -14.750 -1.0476 0.04478 0.04113 -0.0567 1.0000 0.0165 -14.500 -1.0548 0.04148 0.03768 -0.0576 1.0000 0.0167 -14.250 -1.0588 0.03888 0.03495 -0.0575 1.0000 0.0169 -14.000 -1.0634 0.03648 0.03238 -0.0566 1.0000 0.0172 -13.750 -1.0643 0.03460 0.03034 -0.0552 1.0000 0.0176 -13.500 -1.0644 0.03288 0.02845 -0.0533 1.0000 0.0179 -13.250 -1.0635 0.03130 0.02670 -0.0510 1.0000 0.0182 -13.000 -1.0589 0.03007 0.02529 -0.0487 1.0000 0.0185 -12.750 -1.0547 0.02892 0.02406 -0.0461 1.0000 0.0188 -12.500 -1.0457 0.02824 0.02334 -0.0438 1.0000 0.0191 -12.250 -1.0359 0.02766 0.02271 -0.0413 1.0000 0.0193 -12.000 -1.0246 0.02717 0.02218 -0.0390 1.0000 0.0197 -11.750 -1.0116 0.02653 0.02147 -0.0369 1.0000 0.0200 -11.500 -0.9972 0.02591 0.02078 -0.0351 1.0000 0.0205 -11.250 -0.9829 0.02517 0.01994 -0.0332 1.0000 0.0209 -11.000 -0.9677 0.02444 0.01910 -0.0315 1.0000 0.0214 -10.750 -0.9520 0.02370 0.01824 -0.0297 1.0000 0.0219 -10.500 -0.9351 0.02307 0.01750 -0.0280 1.0000 0.0224 -10.250 -0.9177 0.02248 0.01679 -0.0264 1.0000 0.0228 -10.000 -0.9008 0.02177 0.01597 -0.0247 1.0000 0.0231 -9.750 -0.8766 0.02067 0.01481 -0.0248 0.9823 0.0237 -9.500 -0.8304 0.01984 0.01392 -0.0294 0.9421 0.0244 -9.250 -0.7860 0.01912 0.01307 -0.0334 0.9084 0.0251 -9.000 -0.7598 0.01860 0.01238 -0.0334 0.8779 0.0257 -8.750 -0.7383 0.01813 0.01176 -0.0323 0.8550 0.0262 -8.500 -0.7170 0.01771 0.01120 -0.0311 0.8371 0.0268 -8.250 -0.6953 0.01729 0.01064 -0.0300 0.8218 0.0273 -8.000 -0.6733 0.01685 0.01008 -0.0289 0.8081 0.0277 -7.750 -0.6509 0.01643 0.00954 -0.0279 0.7956 0.0280 -7.500 -0.6283 0.01604 0.00904 -0.0269 0.7838 0.0283 -7.250 -0.6069 0.01544 0.00835 -0.0258 0.7726 0.0288 -7.000 -0.5854 0.01486 0.00771 -0.0247 0.7619 0.0295 -6.750 -0.5629 0.01444 0.00721 -0.0237 0.7519 0.0300 -6.500 -0.5398 0.01406 0.00677 -0.0228 0.7417 0.0305 -6.250 -0.5164 0.01371 0.00635 -0.0219 0.7323 0.0310 -6.000 -0.4927 0.01339 0.00596 -0.0211 0.7231 0.0315 -5.750 -0.4686 0.01308 0.00559 -0.0203 0.7141 0.0321 -5.500 -0.4445 0.01281 0.00525 -0.0195 0.7056 0.0327 -5.250 -0.4199 0.01254 0.00493 -0.0189 0.6971 0.0334 -5.000 -0.3952 0.01232 0.00462 -0.0182 0.6891 0.0340 -4.750 -0.3700 0.01210 0.00435 -0.0176 0.6811 0.0347 -4.500 -0.3453 0.01186 0.00406 -0.0169 0.6736 0.0353 -4.250 -0.3203 0.01160 0.00375 -0.0163 0.6660 0.0365 -4.000 -0.2952 0.01140 0.00351 -0.0157 0.6590 0.0378 -3.750 -0.2696 0.01121 0.00330 -0.0151 0.6518 0.0393 -3.500 -0.2440 0.01105 0.00309 -0.0146 0.6447 0.0412 -3.250 -0.2183 0.01089 0.00291 -0.0141 0.6381 0.0444 -3.000 -0.1931 0.01067 0.00272 -0.0135 0.6310 0.0536 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0.00767 0.00221 -0.0106 0.4729 0.9386 2.250 0.3829 0.00780 0.00230 -0.0107 0.4632 0.9471 2.500 0.4184 0.00797 0.00242 -0.0123 0.4526 0.9508 2.750 0.4501 0.00810 0.00252 -0.0131 0.4423 0.9556 3.000 0.4776 0.00824 0.00262 -0.0130 0.4324 0.9609 3.250 0.5114 0.00839 0.00272 -0.0143 0.4196 0.9630 3.500 0.5438 0.00855 0.00283 -0.0154 0.4072 0.9659 3.750 0.5739 0.00868 0.00295 -0.0159 0.3974 0.9698 4.000 0.6031 0.00884 0.00308 -0.0162 0.3870 0.9736 4.250 0.6367 0.00901 0.00321 -0.0176 0.3749 0.9756 4.500 0.6692 0.00917 0.00334 -0.0187 0.3626 0.9782 4.750 0.6993 0.00935 0.00349 -0.0193 0.3494 0.9814 5.000 0.7283 0.00958 0.00367 -0.0198 0.3328 0.9845 5.250 0.7604 0.00983 0.00383 -0.0210 0.3130 0.9862 5.500 0.7918 0.01007 0.00401 -0.0220 0.2947 0.9884 5.750 0.8217 0.01038 0.00424 -0.0227 0.2712 0.9908 6.000 0.8502 0.01073 0.00449 -0.0233 0.2468 0.9932 6.250 0.8801 0.01109 0.00476 -0.0241 0.2230 0.9951 6.500 0.9093 0.01157 0.00509 -0.0250 0.1897 0.9972 6.750 0.9370 0.01222 0.00553 -0.0257 0.1498 0.9992 7.000 0.9603 0.01269 0.00591 -0.0253 0.1321 1.0000 7.250 0.9782 0.01310 0.00628 -0.0236 0.1217 1.0000 7.500 0.9967 0.01344 0.00662 -0.0221 0.1137 1.0000 7.750 1.0145 0.01383 0.00699 -0.0204 0.1062 1.0000 8.000 1.0321 0.01422 0.00736 -0.0188 0.0956 1.0000 8.250 1.0479 0.01470 0.00777 -0.0168 0.0757 1.0000 8.500 1.0576 0.01554 0.00842 -0.0140 0.0515 1.0000 8.750 1.0716 0.01607 0.00895 -0.0118 0.0448 1.0000 9.000 1.0853 0.01659 0.00947 -0.0096 0.0402 1.0000 9.250 1.0993 0.01707 0.00997 -0.0074 0.0372 1.0000 9.500 1.1113 0.01762 0.01054 -0.0049 0.0346 1.0000 9.750 1.1237 0.01813 0.01109 -0.0025 0.0325 1.0000 10.000 1.1350 0.01864 0.01164 0.0001 0.0307 1.0000 10.250 1.1399 0.01921 0.01223 0.0037 0.0288 1.0000 10.500 1.1427 0.01985 0.01289 0.0076 0.0274 1.0000 10.750 1.1504 0.02044 0.01355 0.0103 0.0263 1.0000 11.000 1.1577 0.02118 0.01434 0.0128 0.0249 1.0000 11.250 1.1648 0.02206 0.01527 0.0150 0.0236 1.0000 11.500 1.1704 0.02317 0.01641 0.0170 0.0222 1.0000 11.750 1.1790 0.02420 0.01751 0.0185 0.0212 1.0000 12.000 1.1874 0.02534 0.01871 0.0198 0.0202 1.0000 12.250 1.1952 0.02660 0.02003 0.0209 0.0192 1.0000 12.500 1.2015 0.02806 0.02152 0.0220 0.0181 1.0000 12.750 1.2067 0.02970 0.02322 0.0229 0.0174 1.0000 13.000 1.2132 0.03129 0.02490 0.0236 0.0167 1.0000 13.250 1.2186 0.03303 0.02672 0.0242 0.0163 1.0000 13.500 1.2237 0.03487 0.02862 0.0247 0.0155 1.0000 13.750 1.2277 0.03686 0.03066 0.0251 0.0148 1.0000 14.000 1.2295 0.03910 0.03296 0.0254 0.0143 1.0000 14.250 1.2297 0.04159 0.03552 0.0256 0.0138 1.0000 14.500 1.2305 0.04406 0.03809 0.0256 0.0136 1.0000 14.750 1.2332 0.04637 0.04049 0.0256 0.0130 1.0000 15.000 1.2333 0.04903 0.04324 0.0254 0.0128 1.0000 15.250 1.2328 0.05186 0.04616 0.0251 0.0125 1.0000 15.500 1.2306 0.05499 0.04938 0.0247 0.0122 1.0000 15.750 1.2289 0.05813 0.05261 0.0241 0.0119 1.0000 16.000 1.2269 0.06141 0.05597 0.0233 0.0117 1.0000 16.250 1.2225 0.06506 0.05970 0.0224 0.0114 1.0000 16.500 1.2182 0.06882 0.06354 0.0214 0.0112 1.0000 16.750 1.2113 0.07299 0.06780 0.0201 0.0110 1.0000 17.000 1.2032 0.07741 0.07231 0.0187 0.0108 1.0000 17.250 1.1979 0.08153 0.07652 0.0174 0.0107 1.0000 17.500 1.1928 0.08568 0.08078 0.0159 0.0105 1.0000 17.750 1.1869 0.08998 0.08518 0.0144 0.0104 1.0000 18.000 1.1801 0.09449 0.08979 0.0128 0.0103 1.0000 18.250 1.1753 0.09879 0.09420 0.0111 0.0100 1.0000 18.500 1.1674 0.10359 0.09910 0.0092 0.0099 1.0000 18.750 1.1616 0.10814 0.10374 0.0074 0.0097 1.0000 19.000 1.1524 0.11326 0.10896 0.0052 0.0097 1.0000 19.250 1.1463 0.11801 0.11380 0.0031 0.0094 1.0000