XFOIL Version 6.96 Calculated polar for: EPPLER E838 HYDROFOIL 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 ------ -------- --------- --------- -------- -------- -------- -18.500 -0.7426 0.14771 0.14406 -0.0064 1.0000 0.0099 -18.250 -0.7930 0.13008 0.12613 -0.0164 1.0000 0.0094 -18.000 -0.8182 0.11996 0.11579 -0.0223 1.0000 0.0095 -17.750 -0.8368 0.11190 0.10753 -0.0268 1.0000 0.0094 -17.500 -0.8523 0.10485 0.10028 -0.0305 1.0000 0.0095 -17.250 -0.8655 0.09855 0.09379 -0.0336 1.0000 0.0095 -17.000 -0.8766 0.09287 0.08793 -0.0363 1.0000 0.0097 -16.750 -0.8856 0.08775 0.08261 -0.0383 1.0000 0.0096 -16.500 -0.8923 0.08317 0.07786 -0.0401 1.0000 0.0098 -16.250 -0.8979 0.07888 0.07339 -0.0414 1.0000 0.0099 -16.000 -0.9011 0.07506 0.06940 -0.0426 1.0000 0.0103 -15.750 -0.9024 0.07159 0.06576 -0.0432 1.0000 0.0102 -15.500 -0.9024 0.06838 0.06238 -0.0439 1.0000 0.0106 -15.250 -0.9011 0.06541 0.05920 -0.0445 1.0000 0.0112 -15.000 -0.8977 0.06274 0.05636 -0.0448 1.0000 0.0115 -14.750 -0.8940 0.06024 0.05377 -0.0449 1.0000 0.0118 -14.500 -0.8904 0.05783 0.05131 -0.0451 1.0000 0.0124 -14.250 -0.8840 0.05572 0.04912 -0.0450 1.0000 0.0125 -14.000 -0.8781 0.05360 0.04693 -0.0449 1.0000 0.0130 -13.750 -0.8708 0.05167 0.04491 -0.0448 1.0000 0.0134 -13.500 -0.8634 0.04978 0.04294 -0.0445 1.0000 0.0139 -13.250 -0.8559 0.04794 0.04101 -0.0441 1.0000 0.0145 -13.000 -0.8477 0.04620 0.03915 -0.0437 1.0000 0.0153 -12.750 -0.8411 0.04438 0.03726 -0.0432 1.0000 0.0158 -12.500 -0.8355 0.04252 0.03539 -0.0427 1.0000 0.0166 -12.250 -0.8275 0.04090 0.03374 -0.0424 1.0000 0.0177 -12.000 -0.8181 0.03944 0.03221 -0.0420 1.0000 0.0189 -11.750 -0.8087 0.03799 0.03068 -0.0415 1.0000 0.0203 -11.500 -0.7906 0.03598 0.02855 -0.0440 0.9156 0.0221 -11.250 -0.7749 0.03444 0.02685 -0.0449 0.8867 0.0240 -10.750 -0.7548 0.03184 0.02397 -0.0436 0.8527 0.0284 -10.500 -0.7463 0.03057 0.02265 -0.0427 0.8406 0.0316 -10.250 -0.7357 0.02950 0.02145 -0.0417 0.8305 0.0356 -10.000 -0.7296 0.02824 0.02014 -0.0402 0.8218 0.0405 -9.750 -0.7210 0.02712 0.01897 -0.0389 0.8137 0.0471 -9.500 -0.7139 0.02595 0.01777 -0.0374 0.8069 0.0562 -9.250 -0.7068 0.02479 0.01663 -0.0359 0.7998 0.0682 -9.000 -0.7020 0.02357 0.01545 -0.0341 0.7936 0.0858 -8.750 -0.6973 0.02236 0.01432 -0.0322 0.7874 0.1073 -8.500 -0.6943 0.02115 0.01319 -0.0300 0.7817 0.1321 -8.250 -0.6937 0.01992 0.01206 -0.0273 0.7768 0.1633 -8.000 -0.6951 0.01868 0.01096 -0.0242 0.7710 0.1980 -7.750 -0.7007 0.01746 0.00991 -0.0202 0.7658 0.2392 -7.500 -0.7085 0.01647 0.00909 -0.0151 0.7612 0.2821 -7.250 -0.7160 0.01552 0.00842 -0.0098 0.7561 0.3372 -7.000 -0.7178 0.01468 0.00793 -0.0053 0.7519 0.4066 -6.750 -0.7080 0.01427 0.00776 -0.0023 0.7485 0.4694 -6.500 -0.6897 0.01416 0.00775 -0.0007 0.7444 0.5071 -6.250 -0.6679 0.01412 0.00764 0.0002 0.7403 0.5287 -6.000 -0.6444 0.01411 0.00755 0.0009 0.7368 0.5437 -5.750 -0.6205 0.01416 0.00752 0.0016 0.7340 0.5587 -5.500 -0.5961 0.01426 0.00755 0.0022 0.7307 0.5730 -5.250 -0.5721 0.01434 0.00754 0.0028 0.7268 0.5855 -5.000 -0.5443 0.01449 0.00764 0.0028 0.7234 0.5932 -4.750 -0.5196 0.01447 0.00748 0.0032 0.7204 0.6009 -4.500 -0.4914 0.01453 0.00747 0.0031 0.7180 0.6054 -4.250 -0.4651 0.01449 0.00736 0.0031 0.7145 0.6105 -4.000 -0.4395 0.01440 0.00715 0.0032 0.7110 0.6152 -3.750 -0.4112 0.01439 0.00708 0.0029 0.7078 0.6181 -3.500 -0.3837 0.01435 0.00696 0.0028 0.7051 0.6214 -3.250 -0.3569 0.01429 0.00679 0.0027 0.7027 0.6252 -3.000 -0.3312 0.01419 0.00661 0.0027 0.6992 0.6293 -2.750 -0.3029 0.01417 0.00657 0.0024 0.6959 0.6316 -2.500 -0.2749 0.01415 0.00651 0.0021 0.6929 0.6343 -2.250 -0.2474 0.01411 0.00640 0.0020 0.6903 0.6376 -2.000 -0.2204 0.01405 0.00624 0.0018 0.6881 0.6411 -1.750 -0.1937 0.01400 0.00617 0.0016 0.6846 0.6444 -1.500 -0.1656 0.01400 0.00617 0.0014 0.6813 0.6468 -1.250 -0.1377 0.01399 0.00614 0.0011 0.6783 0.6494 -1.000 -0.1100 0.01396 0.00607 0.0009 0.6757 0.6524 -0.750 -0.0825 0.01393 0.00597 0.0007 0.6736 0.6559 -0.500 -0.0557 0.01391 0.00596 0.0005 0.6703 0.6592 -0.250 -0.0279 0.01393 0.00600 0.0003 0.6668 0.6614 0.000 0.0000 0.01393 0.00601 0.0000 0.6638 0.6639 0.250 0.0279 0.01392 0.00600 -0.0003 0.6614 0.6669 0.500 0.0557 0.01391 0.00595 -0.0005 0.6591 0.6703 0.750 0.0825 0.01393 0.00597 -0.0007 0.6558 0.6737 1.000 0.1100 0.01396 0.00607 -0.0009 0.6523 0.6758 1.250 0.1377 0.01399 0.00614 -0.0011 0.6494 0.6783 1.500 0.1656 0.01400 0.00617 -0.0014 0.6467 0.6813 1.750 0.1937 0.01400 0.00617 -0.0016 0.6444 0.6847 2.000 0.2203 0.01405 0.00624 -0.0018 0.6411 0.6882 2.250 0.2474 0.01411 0.00640 -0.0020 0.6375 0.6903 2.500 0.2749 0.01415 0.00651 -0.0021 0.6343 0.6929 2.750 0.3029 0.01417 0.00657 -0.0024 0.6316 0.6960 3.000 0.3312 0.01419 0.00661 -0.0027 0.6293 0.6993 3.250 0.3569 0.01429 0.00679 -0.0027 0.6252 0.7028 3.500 0.3836 0.01435 0.00697 -0.0028 0.6214 0.7051 3.750 0.4112 0.01439 0.00709 -0.0029 0.6181 0.7079 4.000 0.4395 0.01440 0.00715 -0.0032 0.6152 0.7110 4.250 0.4651 0.01450 0.00736 -0.0031 0.6105 0.7145 4.750 0.5196 0.01447 0.00748 -0.0032 0.6009 0.7205 5.000 0.5443 0.01450 0.00764 -0.0028 0.5932 0.7235 5.250 0.5721 0.01435 0.00754 -0.0028 0.5855 0.7269 5.500 0.5960 0.01427 0.00756 -0.0022 0.5730 0.7308 5.750 0.6205 0.01416 0.00752 -0.0016 0.5588 0.7341 6.000 0.6444 0.01411 0.00755 -0.0009 0.5438 0.7369 6.250 0.6679 0.01412 0.00764 -0.0002 0.5287 0.7404 6.500 0.6896 0.01416 0.00775 0.0007 0.5065 0.7445 6.750 0.7080 0.01427 0.00776 0.0023 0.4691 0.7486 7.000 0.7179 0.01467 0.00793 0.0053 0.4068 0.7519 7.250 0.7157 0.01553 0.00843 0.0099 0.3362 0.7562 7.500 0.7085 0.01647 0.00909 0.0151 0.2819 0.7613 7.750 0.7006 0.01746 0.00991 0.0202 0.2389 0.7659 8.000 0.6954 0.01867 0.01095 0.0242 0.1980 0.7711 8.250 0.6935 0.01994 0.01207 0.0273 0.1623 0.7769 8.500 0.6943 0.02116 0.01319 0.0300 0.1314 0.7817 8.750 0.6975 0.02236 0.01431 0.0322 0.1071 0.7874 9.000 0.7022 0.02357 0.01545 0.0341 0.0854 0.7937 9.250 0.7073 0.02477 0.01661 0.0359 0.0686 0.7998 9.500 0.7141 0.02596 0.01777 0.0374 0.0554 0.8070 9.750 0.7215 0.02711 0.01895 0.0389 0.0469 0.8137 10.000 0.7303 0.02821 0.02012 0.0401 0.0407 0.8218 10.250 0.7364 0.02948 0.02143 0.0416 0.0354 0.8306 10.500 0.7467 0.03058 0.02265 0.0426 0.0317 0.8408 10.750 0.7549 0.03186 0.02399 0.0436 0.0284 0.8530 11.000 0.7642 0.03314 0.02539 0.0444 0.0259 0.8676 11.250 0.7757 0.03442 0.02683 0.0448 0.0241 0.8870 11.500 0.7916 0.03597 0.02853 0.0438 0.0220 0.9161 11.750 0.8092 0.03799 0.03067 0.0414 0.0205 1.0000 12.000 0.8186 0.03944 0.03221 0.0419 0.0193 1.0000 12.250 0.8283 0.04089 0.03373 0.0423 0.0178 1.0000 12.500 0.8363 0.04251 0.03538 0.0427 0.0167 1.0000 12.750 0.8424 0.04433 0.03723 0.0431 0.0160 1.0000 13.000 0.8487 0.04618 0.03913 0.0436 0.0151 1.0000 13.250 0.8571 0.04790 0.04095 0.0440 0.0147 1.0000 13.500 0.8649 0.04971 0.04286 0.0443 0.0142 1.0000 13.750 0.8725 0.05158 0.04482 0.0446 0.0136 1.0000 14.000 0.8793 0.05356 0.04688 0.0448 0.0130 1.0000 14.250 0.8857 0.05564 0.04904 0.0449 0.0126 1.0000 14.500 0.8908 0.05787 0.05133 0.0448 0.0121 1.0000 14.750 0.8967 0.06006 0.05361 0.0448 0.0120 1.0000 15.000 0.8997 0.06264 0.05627 0.0447 0.0116 1.0000 15.250 0.9029 0.06533 0.05910 0.0445 0.0113 1.0000 15.500 0.9047 0.06822 0.06219 0.0439 0.0109 1.0000 15.750 0.9035 0.07159 0.06576 0.0432 0.0104 1.0000 16.000 0.9035 0.07487 0.06918 0.0425 0.0104 1.0000 16.250 0.8992 0.07885 0.07336 0.0413 0.0100 1.0000 16.500 0.8944 0.08302 0.07770 0.0400 0.0099 1.0000 16.750 0.8868 0.08775 0.08262 0.0382 0.0097 1.0000 17.000 0.8783 0.09280 0.08786 0.0361 0.0096 1.0000 17.250 0.8682 0.09830 0.09354 0.0335 0.0095 1.0000 17.500 0.8545 0.10467 0.10010 0.0304 0.0094 1.0000 17.750 0.8388 0.11176 0.10738 0.0267 0.0094 1.0000 18.000 0.8189 0.12013 0.11596 0.0220 0.0095 1.0000 18.250 0.7921 0.13063 0.12670 0.0160 0.0096 1.0000 18.500 0.7476 0.14678 0.14311 0.0068 0.0100 1.0000