GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 693 AIRFOIL (goe693-il) Reynolds number: 500,000 Max Cl/Cd: 87.21 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe693-il-500000-n5.txt Download as CSV file: xf-goe693-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 693 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
------ -------- --------- --------- -------- -------- --------
-14.250 -1.0128 0.03859 0.03521 -0.0888 1.0000 0.0181
-14.000 -1.0304 0.03528 0.03171 -0.0878 1.0000 0.0183
-13.750 -1.0345 0.03312 0.02937 -0.0859 1.0000 0.0186
-13.500 -1.0348 0.03147 0.02758 -0.0836 1.0000 0.0190
-13.250 -1.0306 0.03026 0.02630 -0.0812 1.0000 0.0194
-13.000 -1.0227 0.02931 0.02528 -0.0790 0.9999 0.0198
-12.750 -0.9973 0.02826 0.02413 -0.0801 0.9976 0.0204
-12.500 -0.9715 0.02716 0.02290 -0.0812 0.9954 0.0211
-12.250 -0.9455 0.02603 0.02161 -0.0823 0.9934 0.0218
-12.000 -0.9203 0.02497 0.02038 -0.0830 0.9905 0.0225
-11.750 -0.8930 0.02405 0.01927 -0.0840 0.9880 0.0230
-11.500 -0.8660 0.02296 0.01810 -0.0851 0.9857 0.0238
-11.250 -0.8366 0.02223 0.01730 -0.0863 0.9838 0.0245
-11.000 -0.8108 0.02159 0.01659 -0.0865 0.9797 0.0251
-10.750 -0.7829 0.02094 0.01584 -0.0872 0.9762 0.0258
-10.500 -0.7540 0.02028 0.01506 -0.0880 0.9733 0.0266
-10.250 -0.7278 0.01965 0.01431 -0.0882 0.9690 0.0273
-10.000 -0.7013 0.01908 0.01360 -0.0883 0.9642 0.0279
-9.750 -0.6745 0.01829 0.01270 -0.0886 0.9601 0.0285
-9.500 -0.6506 0.01761 0.01197 -0.0883 0.9541 0.0293
-9.250 -0.6247 0.01711 0.01141 -0.0882 0.9484 0.0300
-9.000 -0.5985 0.01664 0.01088 -0.0880 0.9432 0.0307
-8.750 -0.5735 0.01618 0.01033 -0.0876 0.9359 0.0314
-8.500 -0.5477 0.01570 0.00975 -0.0874 0.9295 0.0321
-8.250 -0.5224 0.01527 0.00924 -0.0869 0.9212 0.0329
-8.000 -0.4965 0.01485 0.00871 -0.0866 0.9137 0.0335
-7.750 -0.4708 0.01444 0.00821 -0.0862 0.9044 0.0339
-7.500 -0.4456 0.01389 0.00758 -0.0858 0.8950 0.0346
-7.250 -0.4200 0.01343 0.00704 -0.0854 0.8842 0.0355
-7.000 -0.3938 0.01306 0.00662 -0.0851 0.8727 0.0364
-6.750 -0.3673 0.01276 0.00623 -0.0848 0.8614 0.0374
-6.500 -0.3406 0.01247 0.00585 -0.0845 0.8502 0.0384
-6.250 -0.3139 0.01219 0.00548 -0.0843 0.8383 0.0393
-6.000 -0.2868 0.01194 0.00514 -0.0841 0.8264 0.0403
-5.750 -0.2598 0.01170 0.00480 -0.0839 0.8154 0.0413
-5.500 -0.2328 0.01142 0.00446 -0.0837 0.8052 0.0432
-5.250 -0.2054 0.01119 0.00419 -0.0836 0.7954 0.0452
-5.000 -0.1778 0.01101 0.00394 -0.0835 0.7865 0.0475
-4.750 -0.1502 0.01083 0.00370 -0.0834 0.7774 0.0503
-4.500 -0.1225 0.01063 0.00348 -0.0834 0.7692 0.0549
-4.250 -0.0947 0.01048 0.00328 -0.0834 0.7614 0.0597
-4.000 -0.0668 0.01032 0.00313 -0.0834 0.7546 0.0669
-3.750 -0.0388 0.01019 0.00300 -0.0834 0.7468 0.0748
-3.500 -0.0108 0.01011 0.00288 -0.0834 0.7391 0.0820
-3.250 0.0173 0.01002 0.00279 -0.0834 0.7307 0.0892
-3.000 0.0455 0.00998 0.00268 -0.0834 0.7233 0.0941
-2.750 0.0736 0.00987 0.00258 -0.0835 0.7158 0.1004
-2.500 0.1018 0.00982 0.00249 -0.0835 0.7092 0.1058
-2.250 0.1303 0.00976 0.00240 -0.0836 0.7022 0.1096
-1.750 0.1865 0.00962 0.00224 -0.0836 0.6860 0.1225
-1.250 0.2427 0.00949 0.00211 -0.0837 0.6699 0.1374
-1.000 0.2706 0.00944 0.00205 -0.0837 0.6613 0.1476
-0.750 0.2987 0.00937 0.00200 -0.0837 0.6514 0.1602
-0.500 0.3266 0.00930 0.00197 -0.0838 0.6433 0.1806
-0.250 0.3547 0.00920 0.00194 -0.0838 0.6365 0.2083
0.000 0.3826 0.00911 0.00193 -0.0839 0.6300 0.2422
0.250 0.4106 0.00898 0.00193 -0.0840 0.6225 0.2852
0.500 0.4379 0.00885 0.00193 -0.0840 0.6145 0.3417
0.750 0.4652 0.00861 0.00195 -0.0840 0.6059 0.4299
1.000 0.4912 0.00828 0.00199 -0.0838 0.5977 0.5613
1.250 0.5157 0.00788 0.00206 -0.0832 0.5886 0.7092
1.500 0.5383 0.00759 0.00213 -0.0818 0.5791 0.8326
1.750 0.5682 0.00752 0.00224 -0.0817 0.5676 0.9416
2.000 0.6060 0.00761 0.00229 -0.0839 0.5541 0.9756
2.250 0.6458 0.00776 0.00235 -0.0866 0.5360 0.9959
2.500 0.6765 0.00792 0.00242 -0.0873 0.5150 1.0000
2.750 0.7002 0.00814 0.00250 -0.0865 0.4884 1.0000
3.000 0.7229 0.00846 0.00263 -0.0855 0.4519 1.0000
3.250 0.7450 0.00885 0.00281 -0.0845 0.4136 1.0000
3.500 0.7682 0.00919 0.00300 -0.0837 0.3852 1.0000
3.750 0.7923 0.00946 0.00317 -0.0830 0.3671 1.0000
4.000 0.8170 0.00970 0.00334 -0.0825 0.3524 1.0000
4.250 0.8420 0.00992 0.00351 -0.0820 0.3406 1.0000
4.500 0.8668 0.01016 0.00369 -0.0815 0.3292 1.0000
4.750 0.8917 0.01039 0.00388 -0.0810 0.3188 1.0000
5.000 0.9169 0.01060 0.00407 -0.0806 0.3095 1.0000
5.250 0.9416 0.01084 0.00428 -0.0801 0.2991 1.0000
5.500 0.9661 0.01110 0.00449 -0.0796 0.2865 1.0000
5.750 0.9907 0.01136 0.00471 -0.0790 0.2731 1.0000
6.000 1.0147 0.01164 0.00495 -0.0785 0.2578 1.0000
6.250 1.0376 0.01200 0.00522 -0.0777 0.2350 1.0000
6.500 1.0582 0.01252 0.00557 -0.0766 0.2022 1.0000
6.750 1.0792 0.01300 0.00595 -0.0756 0.1846 1.0000
7.000 1.1006 0.01343 0.00633 -0.0746 0.1737 1.0000
7.250 1.1226 0.01381 0.00668 -0.0737 0.1659 1.0000
7.500 1.1439 0.01421 0.00707 -0.0727 0.1589 1.0000
7.750 1.1659 0.01456 0.00744 -0.0718 0.1532 1.0000
8.000 1.1871 0.01494 0.00781 -0.0708 0.1449 1.0000
8.250 1.2080 0.01533 0.00819 -0.0698 0.1375 1.0000
8.500 1.2286 0.01571 0.00857 -0.0687 0.1284 1.0000
8.750 1.2473 0.01617 0.00898 -0.0673 0.1120 1.0000
9.000 1.2598 0.01688 0.00953 -0.0649 0.0903 1.0000
9.250 1.2748 0.01746 0.01009 -0.0630 0.0832 1.0000
9.500 1.2898 0.01806 0.01069 -0.0611 0.0764 1.0000
9.750 1.3045 0.01871 0.01134 -0.0592 0.0687 1.0000
10.000 1.3195 0.01935 0.01199 -0.0574 0.0601 1.0000
10.250 1.3268 0.02050 0.01298 -0.0548 0.0394 1.0000
10.500 1.3352 0.02162 0.01405 -0.0524 0.0289 1.0000
10.750 1.3462 0.02261 0.01505 -0.0504 0.0240 1.0000
11.000 1.3574 0.02361 0.01607 -0.0486 0.0209 1.0000
11.250 1.3694 0.02458 0.01710 -0.0470 0.0189 1.0000
11.500 1.3799 0.02570 0.01826 -0.0453 0.0173 1.0000
11.750 1.3917 0.02675 0.01937 -0.0438 0.0164 1.0000
12.000 1.4026 0.02790 0.02059 -0.0424 0.0155 1.0000
12.250 1.4123 0.02918 0.02192 -0.0410 0.0147 1.0000
12.500 1.4204 0.03063 0.02344 -0.0395 0.0139 1.0000
12.750 1.4280 0.03217 0.02506 -0.0382 0.0133 1.0000
13.000 1.4368 0.03364 0.02661 -0.0370 0.0128 1.0000
13.250 1.4445 0.03526 0.02831 -0.0359 0.0123 1.0000
13.500 1.4512 0.03700 0.03013 -0.0349 0.0119 1.0000
13.750 1.4567 0.03889 0.03210 -0.0339 0.0115 1.0000
14.000 1.4607 0.04098 0.03427 -0.0330 0.0112 1.0000
14.250 1.4630 0.04329 0.03666 -0.0322 0.0109 1.0000
14.500 1.4628 0.04591 0.03939 -0.0314 0.0106 1.0000
14.750 1.4625 0.04865 0.04222 -0.0308 0.0103 1.0000
15.000 1.4642 0.05125 0.04493 -0.0304 0.0102 1.0000
15.250 1.4647 0.05404 0.04783 -0.0301 0.0100 1.0000
15.500 1.4641 0.05703 0.05093 -0.0299 0.0098 1.0000
15.750 1.4627 0.06021 0.05421 -0.0299 0.0095 1.0000
16.000 1.4604 0.06361 0.05771 -0.0300 0.0093 1.0000
16.250 1.4575 0.06717 0.06139 -0.0304 0.0091 1.0000
16.500 1.4528 0.07105 0.06537 -0.0309 0.0090 1.0000
16.750 1.4476 0.07510 0.06953 -0.0315 0.0088 1.0000
17.000 1.4414 0.07941 0.07396 -0.0324 0.0087 1.0000
17.250 1.4344 0.08396 0.07862 -0.0335 0.0085 1.0000
17.500 1.4255 0.08886 0.08364 -0.0349 0.0084 1.0000
17.750 1.4156 0.09402 0.08891 -0.0364 0.0083 1.0000
18.000 1.4047 0.09947 0.09447 -0.0382 0.0082 1.0000
18.250 1.3932 0.10508 0.10019 -0.0402 0.0081 1.0000
18.500 1.3806 0.11093 0.10615 -0.0423 0.0081 1.0000
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Polar data table (+)
Polar graphs
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