XFOIL Version 6.96 Calculated polar for: NACA 5-H-10 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 ------ -------- --------- --------- -------- -------- -------- -9.250 -0.5076 0.08715 0.08462 -0.0204 0.8411 0.0188 -9.000 -0.5156 0.08211 0.07959 -0.0243 0.8356 0.0188 -8.750 -0.5264 0.07765 0.07507 -0.0259 0.8303 0.0188 -8.500 -0.5362 0.07393 0.07130 -0.0255 0.8251 0.0188 -8.250 -0.5549 0.06763 0.06492 -0.0254 0.8202 0.0190 -8.000 -0.5632 0.06318 0.06038 -0.0246 0.8159 0.0194 -7.750 -0.5606 0.06011 0.05724 -0.0239 0.8115 0.0197 -7.500 -0.5538 0.05768 0.05474 -0.0233 0.8068 0.0201 -7.250 -0.5455 0.05522 0.05218 -0.0225 0.8026 0.0207 -7.000 -0.5361 0.05248 0.04931 -0.0218 0.7985 0.0217 -6.750 -0.5265 0.04884 0.04551 -0.0208 0.7937 0.0228 -6.500 -0.5067 0.04597 0.04226 -0.0190 0.7894 0.0254 -6.250 -0.4955 0.04266 0.03864 -0.0170 0.7855 0.0255 -6.000 -0.4841 0.03901 0.03469 -0.0150 0.7806 0.0256 -5.750 -0.4709 0.03556 0.03092 -0.0130 0.7762 0.0256 -5.500 -0.4803 0.02150 0.01558 -0.0067 0.7733 0.0198 -5.250 -0.4549 0.02199 0.01619 -0.0068 0.7686 0.0213 -5.000 -0.4312 0.02061 0.01459 -0.0060 0.7637 0.0225 -4.750 -0.4070 0.01882 0.01248 -0.0050 0.7597 0.0236 -4.500 -0.3811 0.01781 0.01125 -0.0043 0.7551 0.0249 -4.250 -0.3555 0.01597 0.00917 -0.0038 0.7501 0.0268 -4.000 -0.3298 0.01522 0.00837 -0.0035 0.7459 0.0290 -3.750 -0.3033 0.01454 0.00760 -0.0032 0.7417 0.0308 -3.500 -0.2765 0.01386 0.00686 -0.0029 0.7365 0.0327 -3.250 -0.2496 0.01361 0.00653 -0.0026 0.7321 0.0347 -3.000 -0.2249 0.01243 0.00524 -0.0020 0.7281 0.0370 -2.750 -0.1997 0.01181 0.00462 -0.0015 0.7229 0.0392 -2.500 -0.1740 0.01145 0.00423 -0.0011 0.7183 0.0418 -2.250 -0.1483 0.01114 0.00386 -0.0006 0.7145 0.0441 -2.000 -0.1223 0.01082 0.00351 -0.0002 0.7095 0.0457 -1.750 -0.0966 0.01050 0.00315 0.0002 0.7051 0.0475 -1.500 -0.0713 0.01016 0.00278 0.0008 0.7015 0.0529 -1.250 -0.0448 0.00997 0.00258 0.0011 0.6966 0.0580 -1.000 -0.0191 0.00968 0.00234 0.0015 0.6915 0.0766 -0.750 -0.0091 0.00805 0.00206 0.0044 0.6873 0.4675 -0.500 -0.0092 0.00689 0.00225 0.0108 0.6827 0.8581 -0.250 0.0137 0.00707 0.00245 0.0125 0.6780 0.8898 0.000 0.0369 0.00722 0.00258 0.0141 0.6742 0.9111 0.250 0.0616 0.00738 0.00274 0.0155 0.6704 0.9269 0.500 0.0943 0.00762 0.00298 0.0151 0.6661 0.9399 0.750 0.1513 0.00807 0.00338 0.0096 0.6621 0.9485 1.000 0.2344 0.00870 0.00392 -0.0016 0.6586 0.9588 1.250 0.2784 0.00881 0.00402 -0.0050 0.6542 0.9617 1.500 0.3081 0.00878 0.00397 -0.0055 0.6477 0.9634 1.750 0.3361 0.00876 0.00392 -0.0057 0.6401 0.9653 2.000 0.3607 0.00871 0.00383 -0.0051 0.6317 0.9666 2.250 0.3834 0.00864 0.00377 -0.0041 0.6230 0.9672 2.500 0.4057 0.00859 0.00367 -0.0031 0.6144 0.9677 2.750 0.4275 0.00851 0.00362 -0.0020 0.6050 0.9684 3.000 0.4480 0.00848 0.00358 -0.0006 0.5978 0.9693 3.250 0.4724 0.00844 0.00356 0.0000 0.5892 0.9701 3.500 0.4992 0.00839 0.00352 0.0001 0.5761 0.9705 3.750 0.5258 0.00837 0.00349 0.0001 0.5599 0.9708 4.000 0.5524 0.00837 0.00348 0.0002 0.5417 0.9713 4.250 0.5787 0.00841 0.00350 0.0003 0.5145 0.9718 4.500 0.6036 0.00862 0.00354 0.0006 0.4560 0.9724 4.750 0.6221 0.00967 0.00397 0.0014 0.3194 0.9734 5.000 0.6390 0.01100 0.00458 0.0021 0.1632 0.9747 5.250 0.6602 0.01176 0.00507 0.0026 0.0997 0.9759 5.500 0.6823 0.01245 0.00550 0.0030 0.0519 0.9774 5.750 0.7056 0.01288 0.00589 0.0034 0.0428 0.9789 6.000 0.7278 0.01325 0.00633 0.0040 0.0398 0.9805 6.250 0.7468 0.01373 0.00684 0.0053 0.0368 0.9824 6.500 0.7691 0.01457 0.00779 0.0055 0.0328 0.9838 6.750 0.7957 0.01509 0.00838 0.0051 0.0314 0.9847 7.000 0.8210 0.01575 0.00911 0.0048 0.0291 0.9859 7.250 0.8448 0.01652 0.00990 0.0046 0.0262 0.9874 7.500 0.8598 0.01845 0.01193 0.0055 0.0237 0.9900 7.750 0.8847 0.01893 0.01248 0.0054 0.0227 0.9918 8.000 0.9077 0.01963 0.01326 0.0056 0.0214 0.9937 8.250 0.9325 0.02048 0.01417 0.0053 0.0200 0.9953 8.500 0.9586 0.02115 0.01486 0.0045 0.0184 0.9970 8.750 0.9781 0.02364 0.01739 0.0049 0.0169 0.9983 9.000 1.0041 0.02457 0.01846 0.0044 0.0164 0.9998 9.250 1.0078 0.02502 0.01902 0.0082 0.0158 1.0000 9.500 1.0057 0.02585 0.01994 0.0132 0.0156 1.0000 9.750 1.0145 0.02689 0.02110 0.0160 0.0150 1.0000 10.000 1.0268 0.02833 0.02268 0.0180 0.0145 1.0000 10.250 1.0379 0.02952 0.02398 0.0200 0.0139 1.0000 10.500 1.0448 0.03011 0.02461 0.0226 0.0133 1.0000 10.750 1.0505 0.03119 0.02580 0.0250 0.0130 1.0000 11.000 1.0559 0.03271 0.02736 0.0270 0.0123 1.0000 11.250 1.0530 0.03701 0.03202 0.0294 0.0120 1.0000 11.500 1.0497 0.03931 0.03455 0.0317 0.0119 1.0000 11.750 1.0447 0.04159 0.03706 0.0338 0.0117 1.0000 12.000 1.0375 0.04440 0.04009 0.0355 0.0117 1.0000 12.250 1.0258 0.04789 0.04381 0.0369 0.0117 1.0000 12.500 1.0116 0.05153 0.04769 0.0378 0.0116 1.0000 12.750 0.9972 0.05532 0.05169 0.0382 0.0114 1.0000 13.000 0.9787 0.05998 0.05654 0.0379 0.0116 1.0000 13.250 0.9607 0.06476 0.06151 0.0368 0.0114 1.0000 13.500 0.9379 0.07068 0.06761 0.0349 0.0115 1.0000 13.750 0.9181 0.07658 0.07364 0.0324 0.0117 1.0000 14.000 0.8131 0.07586 0.07305 0.0346 0.0121 1.0000 14.250 0.7972 0.08201 0.07933 0.0317 0.0122 1.0000 14.500 0.7772 0.08929 0.08675 0.0278 0.0123 1.0000