GOE 615 AIRFOIL (goe615-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 615 AIRFOIL (goe615-il) Reynolds number: 200,000 Max Cl/Cd: 74.63 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe615-il-200000.txt Download as CSV file: xf-goe615-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 615 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.2423 0.13644 0.13266 -0.0414 1.0000 0.0486
-12.250 -0.2483 0.13416 0.13043 -0.0428 1.0000 0.0500
-12.000 -0.2720 0.13259 0.12893 -0.0459 1.0000 0.0505
-11.750 -0.2569 0.12869 0.12507 -0.0431 1.0000 0.0510
-11.500 -0.2499 0.12637 0.12278 -0.0410 1.0000 0.0516
-11.250 -0.2492 0.12473 0.12120 -0.0389 1.0000 0.0524
-11.000 -0.2547 0.12348 0.12000 -0.0365 1.0000 0.0532
-10.750 -0.2638 0.12246 0.11905 -0.0339 1.0000 0.0540
-10.500 -0.2595 0.11968 0.11630 -0.0354 0.9985 0.0554
-10.250 -0.2657 0.11444 0.11106 -0.0489 0.9930 0.0580
-10.000 -0.2451 0.10950 0.10612 -0.0502 0.9900 0.0586
-9.750 -0.2176 0.10616 0.10277 -0.0507 0.9872 0.0597
-9.500 -0.1954 0.10275 0.09935 -0.0539 0.9841 0.0615
-9.250 -0.1798 0.09894 0.09553 -0.0587 0.9794 0.0644
-9.000 -0.1883 0.09204 0.08866 -0.0745 0.9704 0.0671
-8.750 -0.1572 0.08900 0.08560 -0.0724 0.9692 0.0681
-8.500 -0.1371 0.08629 0.08288 -0.0733 0.9627 0.0693
-8.250 -0.1149 0.08288 0.07947 -0.0773 0.9585 0.0717
-8.000 0.0057 0.06352 0.06020 -0.0934 0.9411 0.0807
-7.750 -0.0969 0.07196 0.06854 -0.0953 0.9424 0.0782
-7.500 -0.0626 0.06968 0.06624 -0.0963 0.9409 0.0805
-7.250 -0.0491 0.06638 0.06293 -0.1002 0.9301 0.0835
-7.000 -0.0485 0.05741 0.05377 -0.1162 0.9155 0.0895
-6.750 -0.0188 0.05573 0.05211 -0.1162 0.9112 0.0911
-6.500 -0.0203 0.05167 0.04739 -0.1242 0.8954 0.1010
-6.250 0.0076 0.04704 0.04301 -0.1251 0.8916 0.1029
-6.000 0.0244 0.04600 0.04204 -0.1230 0.8810 0.1048
-5.750 0.0494 0.04397 0.03990 -0.1244 0.8742 0.1103
-5.500 0.0544 0.04052 0.03618 -0.1248 0.8614 0.1182
-5.250 0.0756 0.03905 0.03470 -0.1242 0.8526 0.1213
-5.000 0.0727 0.02747 0.02114 -0.1229 0.8417 0.0772
-4.750 0.0937 0.02561 0.01915 -0.1218 0.8316 0.0758
-4.500 0.1192 0.02356 0.01682 -0.1214 0.8236 0.0748
-4.250 0.1402 0.02204 0.01505 -0.1200 0.8126 0.0737
-4.000 0.1686 0.02062 0.01331 -0.1197 0.8050 0.0731
-3.750 0.1909 0.01965 0.01214 -0.1183 0.7934 0.0732
-3.500 0.2180 0.01884 0.01111 -0.1178 0.7844 0.0743
-3.250 0.2440 0.01824 0.01032 -0.1170 0.7740 0.0757
-3.000 0.2699 0.01771 0.00961 -0.1162 0.7637 0.0766
-2.750 0.2974 0.01675 0.00857 -0.1158 0.7546 0.0780
-2.500 0.3216 0.01618 0.00802 -0.1149 0.7437 0.0799
-2.250 0.3497 0.01575 0.00753 -0.1146 0.7354 0.0827
-2.000 0.3736 0.01546 0.00720 -0.1135 0.7243 0.0862
-1.750 0.3992 0.01505 0.00674 -0.1128 0.7148 0.0895
-1.500 0.4239 0.01465 0.00635 -0.1119 0.7047 0.0940
-1.250 0.4486 0.01445 0.00611 -0.1110 0.6950 0.1001
-1.000 0.4742 0.01412 0.00576 -0.1103 0.6864 0.1110
-0.750 0.4973 0.01377 0.00555 -0.1092 0.6767 0.1363
-0.500 0.5190 0.01299 0.00551 -0.1081 0.6693 0.3452
-0.250 0.5382 0.01253 0.00559 -0.1064 0.6614 0.5020
0.000 0.6454 0.01149 0.00555 -0.1218 0.6525 1.0000
0.250 0.6677 0.01162 0.00556 -0.1206 0.6448 1.0000
0.500 0.6913 0.01174 0.00554 -0.1196 0.6375 1.0000
0.750 0.7152 0.01189 0.00556 -0.1187 0.6306 1.0000
1.000 0.7379 0.01203 0.00561 -0.1175 0.6230 1.0000
1.250 0.7635 0.01218 0.00560 -0.1169 0.6166 1.0000
1.500 0.7849 0.01233 0.00572 -0.1156 0.6087 1.0000
1.750 0.8097 0.01248 0.00574 -0.1148 0.6018 1.0000
2.000 0.8321 0.01265 0.00587 -0.1136 0.5942 1.0000
2.250 0.8557 0.01280 0.00593 -0.1126 0.5867 1.0000
2.500 0.8792 0.01298 0.00605 -0.1116 0.5792 1.0000
2.750 0.9018 0.01314 0.00615 -0.1104 0.5710 1.0000
3.000 0.9257 0.01334 0.00626 -0.1095 0.5632 1.0000
3.250 0.9475 0.01350 0.00640 -0.1082 0.5543 1.0000
3.500 0.9709 0.01371 0.00652 -0.1072 0.5459 1.0000
3.750 0.9923 0.01388 0.00667 -0.1059 0.5364 1.0000
4.000 1.0142 0.01408 0.00682 -0.1046 0.5267 1.0000
4.250 1.0362 0.01426 0.00691 -0.1034 0.5161 1.0000
4.500 1.0545 0.01441 0.00708 -0.1014 0.5038 1.0000
4.750 1.0743 0.01460 0.00722 -0.0998 0.4918 1.0000
5.000 1.0941 0.01478 0.00732 -0.0981 0.4796 1.0000
5.250 1.1108 0.01494 0.00747 -0.0959 0.4653 1.0000
5.500 1.1275 0.01512 0.00765 -0.0937 0.4505 1.0000
5.750 1.1434 0.01532 0.00781 -0.0914 0.4346 1.0000
6.000 1.1583 0.01557 0.00800 -0.0890 0.4181 1.0000
6.250 1.1728 0.01587 0.00822 -0.0865 0.4024 1.0000
6.500 1.1867 0.01622 0.00850 -0.0840 0.3876 1.0000
6.750 1.1995 0.01662 0.00882 -0.0813 0.3746 1.0000
7.000 1.2119 0.01707 0.00918 -0.0786 0.3632 1.0000
7.250 1.2246 0.01757 0.00958 -0.0760 0.3523 1.0000
7.500 1.2390 0.01805 0.01005 -0.0739 0.3425 1.0000
8.000 1.2687 0.01912 0.01104 -0.0698 0.3256 1.0000
8.250 1.2844 0.01974 0.01156 -0.0681 0.3182 1.0000
8.500 1.2989 0.02024 0.01212 -0.0661 0.3105 1.0000
8.750 1.3139 0.02085 0.01267 -0.0643 0.3035 1.0000
9.000 1.3275 0.02143 0.01328 -0.0624 0.2961 1.0000
9.250 1.3407 0.02203 0.01390 -0.0605 0.2891 1.0000
9.500 1.3557 0.02269 0.01453 -0.0589 0.2832 1.0000
9.750 1.3688 0.02328 0.01522 -0.0570 0.2772 1.0000
10.000 1.3824 0.02395 0.01589 -0.0554 0.2718 1.0000
10.250 1.3968 0.02465 0.01661 -0.0538 0.2668 1.0000
10.500 1.4088 0.02534 0.01741 -0.0521 0.2614 1.0000
10.750 1.4205 0.02611 0.01819 -0.0504 0.2562 1.0000
11.000 1.4327 0.02691 0.01901 -0.0488 0.2512 1.0000
11.250 1.4419 0.02777 0.02000 -0.0470 0.2452 1.0000
11.500 1.4520 0.02867 0.02093 -0.0453 0.2403 1.0000
11.750 1.4624 0.02963 0.02192 -0.0438 0.2355 1.0000
12.000 1.4710 0.03065 0.02309 -0.0422 0.2300 1.0000
12.250 1.4764 0.03188 0.02432 -0.0405 0.2237 1.0000
12.500 1.4841 0.03308 0.02562 -0.0391 0.2181 1.0000
12.750 1.4886 0.03450 0.02713 -0.0376 0.2110 1.0000
13.000 1.4927 0.03603 0.02870 -0.0363 0.2047 1.0000
13.250 1.4968 0.03766 0.03044 -0.0351 0.1970 1.0000
13.500 1.4984 0.03956 0.03239 -0.0339 0.1892 1.0000
13.750 1.5000 0.04157 0.03447 -0.0329 0.1809 1.0000
14.000 1.5006 0.04377 0.03674 -0.0320 0.1716 1.0000
14.250 1.4977 0.04641 0.03940 -0.0312 0.1620 1.0000
14.500 1.4932 0.04935 0.04236 -0.0306 0.1509 1.0000
14.750 1.4882 0.05247 0.04549 -0.0302 0.1390 1.0000
15.000 1.4813 0.05592 0.04896 -0.0299 0.1278 1.0000
15.250 1.4742 0.05951 0.05256 -0.0298 0.1187 1.0000
15.500 1.4642 0.06353 0.05659 -0.0299 0.1113 1.0000
15.750 1.4574 0.06728 0.06037 -0.0300 0.1055 1.0000
16.250 1.4440 0.07497 0.06816 -0.0308 0.0981 1.0000
16.500 1.4389 0.07871 0.07197 -0.0313 0.0956 1.0000
16.750 1.4325 0.08267 0.07598 -0.0319 0.0933 1.0000
17.000 1.4254 0.08678 0.08013 -0.0326 0.0913 1.0000
17.250 1.4225 0.09035 0.08378 -0.0333 0.0895 1.0000
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