GOE 621 AIRFOIL (goe621-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 621 AIRFOIL (goe621-il) Reynolds number: 200,000 Max Cl/Cd: 74.72 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe621-il-200000.txt Download as CSV file: xf-goe621-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 621 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1503 0.09027 0.08665 -0.0828 0.9661 0.0939
-9.000 -0.1252 0.08779 0.08416 -0.0843 0.9611 0.0957
-8.750 -0.2427 0.05156 0.04755 -0.1252 0.9397 0.0733
-8.500 -0.3176 0.03787 0.03264 -0.1256 0.9153 0.0648
-8.250 -0.3031 0.03452 0.02875 -0.1260 0.9090 0.0643
-8.000 -0.2918 0.03225 0.02617 -0.1244 0.8996 0.0644
-7.750 -0.2719 0.02982 0.02347 -0.1242 0.8936 0.0647
-7.500 -0.2442 0.02794 0.02143 -0.1249 0.8902 0.0655
-7.250 -0.2294 0.02702 0.02042 -0.1228 0.8801 0.0665
-7.000 -0.2019 0.02581 0.01908 -0.1229 0.8755 0.0677
-6.750 -0.1770 0.02457 0.01763 -0.1225 0.8703 0.0689
-6.500 -0.1579 0.02354 0.01640 -0.1210 0.8618 0.0699
-6.250 -0.1302 0.02240 0.01502 -0.1208 0.8576 0.0712
-6.000 -0.1057 0.02160 0.01401 -0.1201 0.8518 0.0723
-5.750 -0.0832 0.02060 0.01301 -0.1192 0.8448 0.0740
-5.500 -0.0542 0.01991 0.01231 -0.1192 0.8404 0.0765
-5.250 -0.0280 0.01938 0.01169 -0.1187 0.8351 0.0795
-5.000 -0.0049 0.01889 0.01109 -0.1176 0.8281 0.0820
-4.750 0.0227 0.01816 0.01042 -0.1175 0.8237 0.0855
-4.500 0.0521 0.01766 0.00985 -0.1175 0.8199 0.0903
-4.250 0.0720 0.01730 0.00953 -0.1160 0.8122 0.0954
-4.000 0.0998 0.01696 0.00912 -0.1157 0.8074 0.1037
-3.750 0.1288 0.01638 0.00857 -0.1157 0.8039 0.1159
-3.500 0.1490 0.01607 0.00834 -0.1143 0.7972 0.1319
-3.250 0.1736 0.01564 0.00803 -0.1137 0.7917 0.1541
-3.000 0.2036 0.01529 0.00767 -0.1138 0.7875 0.1787
-2.750 0.2266 0.01511 0.00761 -0.1129 0.7809 0.2006
-2.500 0.2524 0.01488 0.00744 -0.1122 0.7742 0.2270
-2.250 0.2829 0.01458 0.00720 -0.1124 0.7694 0.2603
-2.000 0.3050 0.01455 0.00728 -0.1112 0.7622 0.2921
-1.750 0.3318 0.01445 0.00720 -0.1107 0.7559 0.3254
-1.500 0.3629 0.01434 0.00706 -0.1109 0.7511 0.3596
-1.250 0.3835 0.01436 0.00719 -0.1094 0.7429 0.3840
-1.000 0.4118 0.01424 0.00705 -0.1091 0.7366 0.4080
-0.750 0.4397 0.01419 0.00698 -0.1088 0.7312 0.4301
-0.500 0.4626 0.01419 0.00705 -0.1077 0.7244 0.4501
-0.250 0.4908 0.01409 0.00694 -0.1075 0.7189 0.4720
0.000 0.5187 0.01400 0.00690 -0.1073 0.7139 0.4949
0.250 0.5404 0.01397 0.00699 -0.1060 0.7070 0.5196
0.500 0.5674 0.01380 0.00690 -0.1056 0.7012 0.5508
0.750 0.5935 0.01359 0.00685 -0.1049 0.6957 0.5966
1.000 0.6113 0.01312 0.00698 -0.1025 0.6883 0.7302
1.250 0.7370 0.01267 0.00673 -0.1221 0.6812 1.0000
1.500 0.7580 0.01280 0.00681 -0.1206 0.6735 1.0000
1.750 0.7823 0.01285 0.00676 -0.1197 0.6658 1.0000
2.000 0.8067 0.01294 0.00675 -0.1188 0.6586 1.0000
2.250 0.8282 0.01302 0.00680 -0.1174 0.6501 1.0000
2.500 0.8545 0.01306 0.00671 -0.1168 0.6427 1.0000
2.750 0.8738 0.01314 0.00679 -0.1149 0.6325 1.0000
3.000 0.8981 0.01318 0.00674 -0.1140 0.6236 1.0000
3.250 0.9182 0.01323 0.00677 -0.1122 0.6128 1.0000
3.500 0.9390 0.01330 0.00679 -0.1106 0.6017 1.0000
3.750 0.9616 0.01333 0.00673 -0.1093 0.5901 1.0000
4.000 0.9796 0.01340 0.00677 -0.1072 0.5757 1.0000
4.250 0.9972 0.01350 0.00681 -0.1050 0.5596 1.0000
4.500 1.0142 0.01361 0.00685 -0.1027 0.5416 1.0000
4.750 1.0296 0.01378 0.00691 -0.1001 0.5212 1.0000
5.000 1.0426 0.01402 0.00705 -0.0971 0.4977 1.0000
5.250 1.0549 0.01434 0.00721 -0.0940 0.4743 1.0000
5.500 1.0666 0.01475 0.00744 -0.0910 0.4529 1.0000
5.750 1.0783 0.01519 0.00773 -0.0880 0.4336 1.0000
6.000 1.0893 0.01565 0.00805 -0.0849 0.4174 1.0000
6.250 1.1011 0.01614 0.00839 -0.0820 0.4038 1.0000
6.500 1.1144 0.01659 0.00879 -0.0795 0.3916 1.0000
6.750 1.1292 0.01708 0.00919 -0.0773 0.3812 1.0000
7.000 1.1449 0.01759 0.00961 -0.0753 0.3719 1.0000
7.250 1.1615 0.01807 0.01006 -0.0735 0.3634 1.0000
7.500 1.1784 0.01858 0.01051 -0.0718 0.3553 1.0000
7.750 1.1957 0.01910 0.01099 -0.0702 0.3476 1.0000
8.000 1.2117 0.01960 0.01148 -0.0684 0.3401 1.0000
8.250 1.2308 0.02017 0.01197 -0.0672 0.3330 1.0000
8.500 1.2450 0.02067 0.01253 -0.0652 0.3259 1.0000
8.750 1.2639 0.02125 0.01302 -0.0640 0.3192 1.0000
9.000 1.2794 0.02180 0.01362 -0.0623 0.3129 1.0000
9.250 1.2939 0.02236 0.01422 -0.0605 0.3064 1.0000
9.500 1.3150 0.02300 0.01474 -0.0598 0.2999 1.0000
9.750 1.3252 0.02360 0.01547 -0.0574 0.2938 1.0000
10.000 1.3389 0.02422 0.01610 -0.0556 0.2875 1.0000
10.250 1.3555 0.02491 0.01675 -0.0543 0.2812 1.0000
10.500 1.3649 0.02561 0.01756 -0.0521 0.2748 1.0000
10.750 1.3784 0.02632 0.01822 -0.0505 0.2686 1.0000
11.000 1.3894 0.02712 0.01909 -0.0486 0.2622 1.0000
11.250 1.3986 0.02794 0.01998 -0.0466 0.2559 1.0000
11.500 1.4156 0.02870 0.02062 -0.0456 0.2500 1.0000
11.750 1.4210 0.02971 0.02180 -0.0434 0.2440 1.0000
12.000 1.4308 0.03063 0.02275 -0.0417 0.2383 1.0000
12.250 1.4453 0.03152 0.02360 -0.0405 0.2328 1.0000
12.500 1.4518 0.03266 0.02487 -0.0386 0.2272 1.0000
12.750 1.4622 0.03367 0.02589 -0.0372 0.2222 1.0000
13.000 1.4756 0.03466 0.02684 -0.0361 0.2171 1.0000
13.250 1.4810 0.03596 0.02829 -0.0344 0.2121 1.0000
13.500 1.4887 0.03716 0.02951 -0.0331 0.2072 1.0000
13.750 1.5039 0.03811 0.03039 -0.0322 0.2027 1.0000
14.000 1.5056 0.03972 0.03217 -0.0306 0.1982 1.0000
14.250 1.5127 0.04108 0.03360 -0.0294 0.1940 1.0000
14.500 1.5238 0.04222 0.03470 -0.0285 0.1901 1.0000
14.750 1.5318 0.04367 0.03623 -0.0274 0.1863 1.0000
15.000 1.5357 0.04539 0.03809 -0.0263 0.1827 1.0000
15.250 1.5418 0.04696 0.03971 -0.0254 0.1791 1.0000
15.500 1.5523 0.04821 0.04091 -0.0247 0.1755 1.0000
15.750 1.5606 0.04977 0.04256 -0.0239 0.1725 1.0000
16.000 1.5617 0.05189 0.04486 -0.0230 0.1696 1.0000
16.250 1.5657 0.05379 0.04687 -0.0223 0.1666 1.0000
16.500 1.5705 0.05560 0.04871 -0.0218 0.1634 1.0000
16.750 1.5863 0.05650 0.04952 -0.0212 0.1600 1.0000
17.000 1.5819 0.05932 0.05257 -0.0207 0.1578 1.0000
17.250 1.5795 0.06202 0.05544 -0.0203 0.1550 1.0000
17.500 1.5797 0.06450 0.05802 -0.0201 0.1521 1.0000
17.750 1.5832 0.06662 0.06018 -0.0199 0.1493 1.0000
18.000 1.5912 0.06827 0.06180 -0.0196 0.1459 1.0000
18.250 1.5825 0.07197 0.06573 -0.0198 0.1437 1.0000
18.500 1.5759 0.07552 0.06945 -0.0202 0.1409 1.0000
18.750 1.5723 0.07874 0.07276 -0.0206 0.1377 1.0000
19.000 1.5773 0.08078 0.07474 -0.0208 0.1342 1.0000
19.250 1.5670 0.08506 0.07921 -0.0217 0.1316 1.0000
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