GOE 373 AIRFOIL (goe373-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 373 AIRFOIL (goe373-il) Reynolds number: 200,000 Max Cl/Cd: 78.98 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe373-il-200000-n5.txt Download as CSV file: xf-goe373-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 373 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2910 0.08898 0.08574 -0.0214 1.0000 0.0215
-7.000 -0.2933 0.08699 0.08381 -0.0208 1.0000 0.0220
-6.750 -0.2935 0.08486 0.08175 -0.0211 1.0000 0.0224
-6.500 -0.2600 0.08030 0.07714 -0.0322 0.9906 0.0229
-6.250 -0.2169 0.07527 0.07201 -0.0475 0.9794 0.0231
-6.000 -0.2036 0.07103 0.06780 -0.0464 0.9744 0.0234
-5.750 -0.1823 0.06738 0.06414 -0.0492 0.9649 0.0239
-5.500 -0.1540 0.06361 0.06032 -0.0546 0.9547 0.0245
-5.250 -0.1207 0.05968 0.05632 -0.0612 0.9455 0.0255
-5.000 -0.0645 0.05524 0.05161 -0.0742 0.9339 0.0277
-4.750 -0.0067 0.03268 0.02913 -0.0773 0.8831 0.0283
-4.500 0.0130 0.02955 0.02594 -0.0785 0.8688 0.0288
-4.250 0.0356 0.02667 0.02294 -0.0804 0.8532 0.0297
-4.000 0.0606 0.02394 0.02006 -0.0826 0.8372 0.0309
-3.750 0.1013 0.02157 0.01721 -0.0871 0.8217 0.0340
-3.500 0.1257 0.01863 0.01403 -0.0885 0.8052 0.0344
-3.250 0.1448 0.01629 0.01162 -0.0889 0.7885 0.0351
-3.000 0.1673 0.01456 0.00975 -0.0894 0.7732 0.0362
-2.750 0.1927 0.01300 0.00800 -0.0901 0.7601 0.0378
-2.500 0.2265 0.01163 0.00610 -0.0911 0.7483 0.0425
-2.250 0.2476 0.01012 0.00458 -0.0916 0.7358 0.0443
-2.000 0.2729 0.00921 0.00351 -0.0919 0.7222 0.0482
-1.750 0.3003 0.00818 0.00220 -0.0923 0.7089 0.0539
-1.500 0.3267 0.00769 0.00149 -0.0922 0.6944 0.0606
-1.250 0.3518 0.00682 0.00048 -0.0925 0.6807 0.0667
-0.750 0.4192 0.01961 0.01259 -0.0977 0.6745 0.0831
0.250 0.5309 0.01584 0.00757 -0.0949 0.6087 0.0499
0.500 0.5577 0.01507 0.00657 -0.0942 0.5933 0.0444
1.000 0.6102 0.01434 0.00554 -0.0930 0.5652 0.0396
1.250 0.6362 0.01401 0.00509 -0.0924 0.5523 0.0383
1.500 0.6620 0.01376 0.00473 -0.0918 0.5388 0.0373
1.750 0.6877 0.01357 0.00447 -0.0912 0.5248 0.0366
2.000 0.7132 0.01344 0.00427 -0.0906 0.5107 0.0363
2.250 0.7388 0.01332 0.00413 -0.0901 0.4979 0.0364
2.500 0.7643 0.01322 0.00403 -0.0896 0.4859 0.0376
2.750 0.7897 0.01318 0.00398 -0.0892 0.4736 0.0400
3.000 0.8153 0.01319 0.00396 -0.0887 0.4611 0.0404
3.250 0.8410 0.01323 0.00396 -0.0882 0.4479 0.0405
3.500 0.8666 0.01331 0.00399 -0.0877 0.4349 0.0406
3.750 0.8921 0.01342 0.00407 -0.0872 0.4218 0.0409
4.000 0.9175 0.01355 0.00416 -0.0867 0.4092 0.0414
4.500 0.9680 0.01391 0.00444 -0.0857 0.3856 0.0439
4.750 0.9933 0.01408 0.00466 -0.0852 0.3749 0.0499
5.000 1.0228 0.01295 0.00503 -0.0860 0.3620 1.0000
5.250 1.0465 0.01329 0.00527 -0.0853 0.3440 1.0000
5.500 1.0698 0.01366 0.00554 -0.0845 0.3254 1.0000
5.750 1.0932 0.01403 0.00585 -0.0838 0.3058 1.0000
6.000 1.1165 0.01439 0.00616 -0.0831 0.2841 1.0000
6.250 1.1386 0.01486 0.00649 -0.0823 0.2506 1.0000
6.500 1.1559 0.01584 0.00702 -0.0810 0.1821 1.0000
6.750 1.1749 0.01671 0.00766 -0.0798 0.1513 1.0000
7.000 1.1953 0.01741 0.00825 -0.0788 0.1260 1.0000
7.250 1.2088 0.01884 0.00920 -0.0771 0.0631 1.0000
7.500 1.2213 0.02034 0.01042 -0.0751 0.0209 1.0000
7.750 1.2401 0.02113 0.01128 -0.0737 0.0182 1.0000
8.000 1.2592 0.02185 0.01213 -0.0724 0.0167 1.0000
8.250 1.2777 0.02259 0.01301 -0.0711 0.0159 1.0000
8.500 1.2945 0.02346 0.01403 -0.0696 0.0146 1.0000
8.750 1.3098 0.02443 0.01515 -0.0679 0.0137 1.0000
9.000 1.3232 0.02550 0.01641 -0.0659 0.0131 1.0000
9.250 1.3338 0.02670 0.01777 -0.0637 0.0127 1.0000
9.500 1.3389 0.02806 0.01929 -0.0607 0.0123 1.0000
9.750 1.3390 0.02967 0.02105 -0.0574 0.0120 1.0000
10.000 1.3359 0.03155 0.02307 -0.0541 0.0118 1.0000
10.250 1.3361 0.03333 0.02495 -0.0515 0.0116 1.0000
10.500 1.3388 0.03507 0.02681 -0.0496 0.0114 1.0000
10.750 1.3418 0.03692 0.02880 -0.0480 0.0111 1.0000
11.000 1.3435 0.03902 0.03103 -0.0467 0.0108 1.0000
11.250 1.3445 0.04134 0.03347 -0.0456 0.0104 1.0000
11.500 1.3444 0.04392 0.03616 -0.0448 0.0100 1.0000
11.750 1.3436 0.04671 0.03905 -0.0442 0.0098 1.0000
12.000 1.3430 0.04962 0.04206 -0.0438 0.0096 1.0000
12.250 1.3427 0.05258 0.04512 -0.0435 0.0094 1.0000
12.500 1.3431 0.05553 0.04816 -0.0432 0.0093 1.0000
12.750 1.3441 0.05851 0.05125 -0.0430 0.0092 1.0000
13.000 1.3454 0.06150 0.05433 -0.0429 0.0090 1.0000
13.250 1.3472 0.06449 0.05741 -0.0427 0.0089 1.0000
13.500 1.3500 0.06744 0.06045 -0.0426 0.0088 1.0000
13.750 1.3528 0.07043 0.06354 -0.0424 0.0086 1.0000
14.000 1.3559 0.07347 0.06667 -0.0424 0.0086 1.0000
14.250 1.3596 0.07653 0.06983 -0.0423 0.0085 1.0000
14.500 1.3634 0.07970 0.07310 -0.0422 0.0084 1.0000
14.750 1.3648 0.08331 0.07686 -0.0424 0.0083 1.0000
15.000 1.3639 0.08732 0.08103 -0.0430 0.0082 1.0000
15.250 1.3624 0.09167 0.08553 -0.0437 0.0081 1.0000
15.500 1.3522 0.09698 0.09104 -0.0460 0.0081 1.0000
15.750 1.3418 0.10246 0.09673 -0.0488 0.0080 1.0000
16.000 1.3310 0.10824 0.10271 -0.0519 0.0080 1.0000
16.250 1.3194 0.11442 0.10910 -0.0555 0.0080 1.0000
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Polar data table (+)
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