GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 655 AIRFOIL (goe655-il) Reynolds number: 500,000 Max Cl/Cd: 89.48 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe655-il-500000-n5.txt Download as CSV file: xf-goe655-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 655 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8617 0.04040 0.03696 -0.0907 1.0000 0.0185
-13.750 -0.8944 0.03515 0.03153 -0.0932 1.0000 0.0185
-13.500 -0.9089 0.03307 0.02934 -0.0915 0.9988 0.0186
-13.250 -0.8916 0.03130 0.02744 -0.0933 0.9942 0.0190
-13.000 -0.8727 0.02973 0.02573 -0.0945 0.9898 0.0194
-12.750 -0.8504 0.02836 0.02422 -0.0958 0.9862 0.0200
-12.500 -0.8264 0.02690 0.02257 -0.0973 0.9835 0.0206
-12.250 -0.8076 0.02559 0.02105 -0.0973 0.9783 0.0211
-12.000 -0.7821 0.02465 0.02007 -0.0982 0.9751 0.0216
-11.750 -0.7535 0.02394 0.01930 -0.0993 0.9729 0.0220
-11.500 -0.7283 0.02320 0.01850 -0.0997 0.9692 0.0224
-11.250 -0.7027 0.02248 0.01769 -0.1000 0.9648 0.0230
-11.000 -0.6734 0.02173 0.01683 -0.1010 0.9619 0.0236
-10.750 -0.6431 0.02090 0.01585 -0.1023 0.9595 0.0243
-10.500 -0.6183 0.02022 0.01501 -0.1022 0.9539 0.0249
-10.250 -0.5919 0.01938 0.01408 -0.1025 0.9487 0.0254
-10.000 -0.5611 0.01872 0.01338 -0.1036 0.9450 0.0260
-9.750 -0.5354 0.01825 0.01287 -0.1034 0.9380 0.0265
-9.500 -0.5066 0.01775 0.01230 -0.1039 0.9316 0.0272
-9.250 -0.4787 0.01721 0.01167 -0.1041 0.9247 0.0278
-9.000 -0.4526 0.01671 0.01106 -0.1039 0.9160 0.0285
-8.750 -0.4258 0.01621 0.01044 -0.1038 0.9078 0.0291
-8.500 -0.3996 0.01579 0.00990 -0.1035 0.8982 0.0296
-8.250 -0.3759 0.01514 0.00919 -0.1028 0.8881 0.0302
-8.000 -0.3503 0.01468 0.00868 -0.1024 0.8773 0.0308
-7.750 -0.3251 0.01435 0.00827 -0.1019 0.8641 0.0315
-7.500 -0.3001 0.01401 0.00785 -0.1012 0.8486 0.0322
-7.250 -0.2754 0.01368 0.00740 -0.1005 0.8303 0.0327
-7.000 -0.2512 0.01336 0.00696 -0.0997 0.8105 0.0334
-6.750 -0.2271 0.01308 0.00654 -0.0988 0.7900 0.0340
-6.500 -0.2032 0.01287 0.00617 -0.0978 0.7689 0.0346
-6.250 -0.1794 0.01262 0.00579 -0.0969 0.7514 0.0352
-6.000 -0.1555 0.01231 0.00541 -0.0960 0.7375 0.0361
-5.750 -0.1308 0.01208 0.00511 -0.0953 0.7260 0.0369
-5.500 -0.1057 0.01189 0.00484 -0.0946 0.7154 0.0377
-5.250 -0.0801 0.01168 0.00458 -0.0940 0.7061 0.0387
-5.000 -0.0548 0.01152 0.00433 -0.0934 0.6969 0.0397
-4.750 -0.0288 0.01135 0.00410 -0.0928 0.6871 0.0407
-4.500 -0.0035 0.01116 0.00386 -0.0922 0.6770 0.0420
-4.250 0.0220 0.01099 0.00365 -0.0916 0.6658 0.0439
-4.000 0.0479 0.01085 0.00347 -0.0910 0.6549 0.0457
-3.750 0.0737 0.01075 0.00329 -0.0904 0.6441 0.0477
-3.500 0.0994 0.01061 0.00311 -0.0899 0.6323 0.0503
-3.250 0.1252 0.01049 0.00296 -0.0893 0.6199 0.0539
-3.000 0.1508 0.01041 0.00282 -0.0887 0.6067 0.0584
-2.750 0.1761 0.01032 0.00269 -0.0880 0.5921 0.0654
-2.500 0.2010 0.01023 0.00258 -0.0873 0.5763 0.0763
-2.250 0.2255 0.01012 0.00247 -0.0866 0.5594 0.0965
-2.000 0.2497 0.00999 0.00240 -0.0858 0.5428 0.1326
-1.750 0.2742 0.00992 0.00235 -0.0851 0.5272 0.1637
-1.500 0.2989 0.00987 0.00232 -0.0844 0.5120 0.1919
-1.250 0.3235 0.00984 0.00231 -0.0837 0.4971 0.2223
-1.000 0.3484 0.00982 0.00231 -0.0830 0.4822 0.2510
-0.750 0.3732 0.00980 0.00232 -0.0823 0.4677 0.2840
-0.500 0.3977 0.00977 0.00235 -0.0816 0.4538 0.3227
-0.250 0.4220 0.00975 0.00239 -0.0809 0.4397 0.3628
0.000 0.4458 0.00974 0.00244 -0.0801 0.4246 0.4084
0.250 0.4696 0.00975 0.00250 -0.0792 0.4104 0.4525
0.500 0.4936 0.00980 0.00256 -0.0784 0.3960 0.4839
0.750 0.5173 0.00984 0.00262 -0.0775 0.3838 0.5198
1.000 0.5408 0.00980 0.00269 -0.0766 0.3740 0.5712
1.250 0.5622 0.00970 0.00279 -0.0753 0.3658 0.6507
1.500 0.5823 0.00952 0.00289 -0.0735 0.3587 0.7519
1.750 0.6052 0.00935 0.00303 -0.0721 0.3520 0.8716
2.000 0.6857 0.00955 0.00326 -0.0834 0.3438 0.9714
2.250 0.7285 0.00973 0.00338 -0.0867 0.3379 0.9913
2.500 0.7596 0.00993 0.00351 -0.0874 0.3332 1.0000
2.750 0.7826 0.01005 0.00360 -0.0864 0.3290 1.0000
3.000 0.8052 0.01019 0.00369 -0.0853 0.3241 1.0000
3.250 0.8272 0.01036 0.00381 -0.0841 0.3193 1.0000
3.500 0.8496 0.01052 0.00393 -0.0830 0.3154 1.0000
3.750 0.8727 0.01064 0.00405 -0.0820 0.3117 1.0000
4.000 0.8955 0.01079 0.00417 -0.0810 0.3080 1.0000
4.250 0.9177 0.01096 0.00431 -0.0798 0.3038 1.0000
4.500 0.9395 0.01115 0.00446 -0.0786 0.3000 1.0000
4.750 0.9629 0.01128 0.00460 -0.0777 0.2968 1.0000
5.000 0.9858 0.01143 0.00475 -0.0768 0.2932 1.0000
5.250 1.0082 0.01160 0.00491 -0.0757 0.2894 1.0000
5.500 1.0299 0.01180 0.00509 -0.0746 0.2856 1.0000
5.750 1.0523 0.01197 0.00526 -0.0735 0.2823 1.0000
6.000 1.0750 0.01213 0.00543 -0.0726 0.2782 1.0000
6.250 1.0966 0.01233 0.00562 -0.0714 0.2729 1.0000
6.500 1.1173 0.01256 0.00583 -0.0701 0.2680 1.0000
6.750 1.1391 0.01273 0.00602 -0.0690 0.2623 1.0000
7.000 1.1584 0.01296 0.00623 -0.0675 0.2561 1.0000
7.250 1.1777 0.01318 0.00646 -0.0659 0.2503 1.0000
7.500 1.1963 0.01343 0.00669 -0.0643 0.2422 1.0000
7.750 1.2146 0.01371 0.00695 -0.0627 0.2335 1.0000
8.000 1.2318 0.01405 0.00725 -0.0609 0.2232 1.0000
8.250 1.2479 0.01444 0.00760 -0.0590 0.2106 1.0000
8.750 1.2777 0.01540 0.00844 -0.0550 0.1877 1.0000
9.000 1.2925 0.01591 0.00892 -0.0531 0.1802 1.0000
9.250 1.3065 0.01646 0.00945 -0.0511 0.1731 1.0000
9.500 1.3211 0.01700 0.00998 -0.0493 0.1671 1.0000
9.750 1.3368 0.01749 0.01049 -0.0477 0.1634 1.0000
10.000 1.3506 0.01810 0.01109 -0.0459 0.1589 1.0000
10.250 1.3643 0.01871 0.01173 -0.0441 0.1559 1.0000
10.500 1.3807 0.01921 0.01227 -0.0428 0.1534 1.0000
10.750 1.3964 0.01975 0.01286 -0.0414 0.1506 1.0000
11.000 1.4108 0.02038 0.01353 -0.0399 0.1476 1.0000
11.250 1.4233 0.02114 0.01431 -0.0383 0.1441 1.0000
11.500 1.4351 0.02197 0.01516 -0.0367 0.1405 1.0000
11.750 1.4504 0.02260 0.01586 -0.0355 0.1376 1.0000
12.000 1.4639 0.02338 0.01668 -0.0343 0.1341 1.0000
12.250 1.4745 0.02436 0.01769 -0.0329 0.1295 1.0000
12.500 1.4857 0.02534 0.01870 -0.0316 0.1254 1.0000
12.750 1.4960 0.02642 0.01980 -0.0303 0.1180 1.0000
13.000 1.5038 0.02773 0.02111 -0.0290 0.1102 1.0000
13.250 1.5049 0.02961 0.02292 -0.0275 0.0950 1.0000
13.500 1.4916 0.03280 0.02596 -0.0255 0.0710 1.0000
13.750 1.4591 0.03799 0.03100 -0.0234 0.0409 1.0000
14.000 1.4370 0.04266 0.03564 -0.0224 0.0238 1.0000
14.250 1.4293 0.04611 0.03915 -0.0220 0.0195 1.0000
14.500 1.4250 0.04934 0.04247 -0.0219 0.0177 1.0000
14.750 1.4214 0.05260 0.04582 -0.0220 0.0166 1.0000
15.000 1.4166 0.05609 0.04941 -0.0222 0.0156 1.0000
15.250 1.4116 0.05974 0.05316 -0.0226 0.0150 1.0000
15.500 1.4042 0.06378 0.05730 -0.0232 0.0144 1.0000
15.750 1.3963 0.06797 0.06160 -0.0240 0.0140 1.0000
16.000 1.3895 0.07211 0.06585 -0.0248 0.0134 1.0000
16.250 1.3819 0.07645 0.07030 -0.0258 0.0132 1.0000
16.500 1.3731 0.08099 0.07495 -0.0269 0.0130 1.0000
16.750 1.3642 0.08561 0.07969 -0.0281 0.0126 1.0000
17.000 1.3535 0.09059 0.08479 -0.0295 0.0123 1.0000
17.250 1.3425 0.09568 0.08998 -0.0310 0.0121 1.0000
17.500 1.3313 0.10085 0.09526 -0.0326 0.0119 1.0000
17.750 1.3201 0.10609 0.10060 -0.0344 0.0117 1.0000
18.000 1.3068 0.11178 0.10640 -0.0364 0.0115 1.0000
18.250 1.2958 0.11715 0.11187 -0.0384 0.0113 1.0000
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