GOE 735 AIRFOIL (goe735-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 735 AIRFOIL (goe735-il) Reynolds number: 100,000 Max Cl/Cd: 35.9 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe735-il-100000-n5.txt Download as CSV file: xf-goe735-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 735 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3650 0.09407 0.08838 -0.0521 0.8172 0.0791
-12.750 -0.6178 0.05329 0.04702 -0.0787 0.8280 0.0827
-12.500 -0.6560 0.04880 0.04218 -0.0780 0.8176 0.0837
-12.250 -0.6852 0.04554 0.03857 -0.0753 0.8074 0.0849
-12.000 -0.7132 0.04264 0.03524 -0.0711 0.7977 0.0863
-11.750 -0.7035 0.04191 0.03448 -0.0691 0.7880 0.0875
-11.500 -0.6932 0.04134 0.03390 -0.0671 0.7788 0.0889
-11.250 -0.6897 0.04048 0.03292 -0.0643 0.7696 0.0904
-11.000 -0.6895 0.03928 0.03149 -0.0611 0.7614 0.0924
-10.750 -0.6926 0.03765 0.02947 -0.0576 0.7526 0.0947
-10.500 -0.6799 0.03687 0.02858 -0.0556 0.7451 0.0965
-10.250 -0.6626 0.03634 0.02805 -0.0542 0.7356 0.0982
-10.000 -0.6489 0.03564 0.02722 -0.0523 0.7274 0.1005
-9.750 -0.6379 0.03463 0.02593 -0.0501 0.7196 0.1033
-9.500 -0.6248 0.03361 0.02466 -0.0481 0.7108 0.1058
-9.250 -0.6044 0.03314 0.02418 -0.0469 0.7037 0.1078
-9.000 -0.5852 0.03260 0.02359 -0.0457 0.6942 0.1103
-8.750 -0.5682 0.03185 0.02262 -0.0440 0.6863 0.1132
-8.500 -0.5522 0.03099 0.02142 -0.0422 0.6787 0.1162
-8.250 -0.5288 0.03040 0.02091 -0.0415 0.6696 0.1184
-8.000 -0.5074 0.02987 0.02029 -0.0403 0.6626 0.1209
-7.750 -0.4859 0.02929 0.01960 -0.0394 0.6533 0.1238
-7.500 -0.4650 0.02861 0.01867 -0.0381 0.6456 0.1269
-7.250 -0.4419 0.02795 0.01791 -0.0373 0.6380 0.1295
-7.000 -0.4179 0.02743 0.01741 -0.0366 0.6292 0.1321
-6.750 -0.3944 0.02691 0.01676 -0.0357 0.6226 0.1349
-6.500 -0.3704 0.02641 0.01616 -0.0350 0.6137 0.1381
-6.250 -0.3465 0.02591 0.01543 -0.0342 0.6063 0.1413
-6.000 -0.3213 0.02535 0.01488 -0.0337 0.5993 0.1442
-5.750 -0.2964 0.02492 0.01445 -0.0331 0.5911 0.1472
-5.500 -0.2716 0.02448 0.01391 -0.0324 0.5846 0.1508
-5.250 -0.2464 0.02413 0.01343 -0.0318 0.5773 0.1547
-5.000 -0.2212 0.02370 0.01298 -0.0313 0.5701 0.1582
-4.750 -0.1964 0.02331 0.01255 -0.0306 0.5643 0.1620
-4.500 -0.1715 0.02302 0.01224 -0.0300 0.5571 0.1665
-4.250 -0.1463 0.02275 0.01186 -0.0294 0.5503 0.1715
-4.000 -0.1220 0.02237 0.01149 -0.0287 0.5450 0.1763
-3.750 -0.0977 0.02215 0.01127 -0.0280 0.5388 0.1820
-3.500 -0.0729 0.02195 0.01101 -0.0273 0.5324 0.1886
-3.250 -0.0495 0.02165 0.01075 -0.0265 0.5270 0.1956
-3.000 -0.0251 0.02147 0.01051 -0.0257 0.5218 0.2045
-2.750 -0.0020 0.02129 0.01042 -0.0249 0.5156 0.2139
-2.500 0.0219 0.02112 0.01025 -0.0241 0.5103 0.2265
-2.250 0.0457 0.02091 0.01005 -0.0232 0.5060 0.2426
-2.000 0.0688 0.02077 0.01000 -0.0224 0.5010 0.2634
-1.750 0.0912 0.02061 0.01000 -0.0215 0.4954 0.2912
-1.500 0.1141 0.02040 0.00992 -0.0205 0.4904 0.3290
-1.250 0.1371 0.02014 0.00979 -0.0196 0.4863 0.3772
-1.000 0.1586 0.01990 0.00982 -0.0185 0.4819 0.4386
-0.750 0.1794 0.01957 0.00998 -0.0171 0.4771 0.5372
-0.500 0.2117 0.01929 0.01022 -0.0175 0.4723 0.6625
-0.250 0.2820 0.01948 0.01064 -0.0242 0.4671 0.7827
0.000 0.3288 0.01990 0.01105 -0.0272 0.4620 0.8297
0.250 0.3653 0.02032 0.01145 -0.0284 0.4567 0.8595
0.500 0.4014 0.02072 0.01175 -0.0295 0.4524 0.8821
0.750 0.4387 0.02111 0.01200 -0.0308 0.4487 0.9015
1.000 0.4830 0.02160 0.01236 -0.0333 0.4448 0.9220
1.250 0.5286 0.02213 0.01288 -0.0366 0.4395 0.9404
1.500 0.5714 0.02246 0.01314 -0.0394 0.4348 0.9537
1.750 0.6127 0.02269 0.01324 -0.0420 0.4309 0.9655
2.000 0.6612 0.02284 0.01322 -0.0460 0.4277 0.9760
2.250 0.7070 0.02313 0.01353 -0.0501 0.4233 0.9857
2.500 0.7479 0.02336 0.01375 -0.0532 0.4189 0.9938
2.750 0.7853 0.02346 0.01380 -0.0556 0.4150 0.9993
3.000 0.8071 0.02362 0.01387 -0.0549 0.4120 1.0000
3.250 0.8270 0.02377 0.01391 -0.0538 0.4094 1.0000
3.500 0.8434 0.02418 0.01434 -0.0524 0.4063 1.0000
3.750 0.8583 0.02465 0.01487 -0.0509 0.4029 1.0000
4.000 0.8740 0.02507 0.01531 -0.0493 0.3997 1.0000
4.250 0.8908 0.02541 0.01563 -0.0479 0.3968 1.0000
4.500 0.9088 0.02568 0.01585 -0.0465 0.3942 1.0000
4.750 0.9283 0.02590 0.01598 -0.0453 0.3918 1.0000
5.000 0.9444 0.02631 0.01637 -0.0437 0.3892 1.0000
5.250 0.9521 0.02707 0.01725 -0.0412 0.3857 1.0000
5.500 0.9618 0.02773 0.01797 -0.0389 0.3826 1.0000
5.750 0.9735 0.02829 0.01855 -0.0368 0.3799 1.0000
6.000 0.9875 0.02873 0.01897 -0.0349 0.3774 1.0000
6.250 1.0047 0.02905 0.01924 -0.0334 0.3752 1.0000
6.500 1.0257 0.02927 0.01937 -0.0323 0.3731 1.0000
6.750 1.0265 0.03020 0.02040 -0.0289 0.3701 1.0000
7.000 1.0166 0.03148 0.02181 -0.0243 0.3668 1.0000
7.250 1.0096 0.03260 0.02301 -0.0200 0.3637 1.0000
7.500 1.0039 0.03351 0.02394 -0.0158 0.3612 1.0000
7.750 1.0094 0.03409 0.02450 -0.0130 0.3588 1.0000
8.000 1.0296 0.03429 0.02464 -0.0119 0.3568 1.0000
8.250 1.0612 0.03425 0.02452 -0.0121 0.3550 1.0000
8.500 0.8557 0.04729 0.03809 0.0025 0.3428 1.0000
8.750 0.8725 0.04779 0.03856 0.0034 0.3408 1.0000
9.000 0.9008 0.04731 0.03804 0.0041 0.3395 1.0000
9.250 0.9353 0.04639 0.03706 0.0046 0.3386 1.0000
9.500 0.9727 0.04537 0.03597 0.0050 0.3377 1.0000
12.500 0.7139 0.10839 0.09969 0.0036 0.2581 1.0000
12.750 0.7334 0.10869 0.09999 0.0040 0.2571 1.0000
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Polar data table (+)
Polar graphs
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