GOE 767 AIRFOIL (goe767-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 767 AIRFOIL (goe767-il) Reynolds number: 200,000 Max Cl/Cd: 54.86 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe767-il-200000-n5.txt Download as CSV file: xf-goe767-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 767 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
------ -------- --------- --------- -------- -------- --------
-15.000 -1.0210 0.07380 0.06857 -0.0228 1.0000 0.0357
-14.750 -1.0564 0.06369 0.05816 -0.0309 1.0000 0.0357
-14.500 -1.0728 0.05765 0.05195 -0.0351 1.0000 0.0358
-14.250 -1.0849 0.05279 0.04694 -0.0381 1.0000 0.0359
-14.000 -1.0936 0.04885 0.04287 -0.0400 1.0000 0.0360
-13.750 -1.0993 0.04567 0.03958 -0.0409 1.0000 0.0362
-13.500 -1.1034 0.04299 0.03679 -0.0409 1.0000 0.0364
-13.250 -1.1057 0.04075 0.03445 -0.0402 1.0000 0.0367
-13.000 -1.1064 0.03883 0.03242 -0.0389 1.0000 0.0369
-12.750 -1.1057 0.03717 0.03065 -0.0370 1.0000 0.0373
-12.500 -1.1034 0.03572 0.02910 -0.0347 1.0000 0.0377
-12.250 -1.0977 0.03430 0.02756 -0.0327 1.0000 0.0382
-12.000 -1.0885 0.03291 0.02603 -0.0309 1.0000 0.0387
-11.750 -1.0772 0.03158 0.02454 -0.0293 1.0000 0.0392
-11.500 -1.0641 0.03030 0.02311 -0.0277 1.0000 0.0397
-11.250 -1.0493 0.02911 0.02175 -0.0263 1.0000 0.0401
-11.000 -1.0337 0.02797 0.02057 -0.0249 1.0000 0.0406
-10.750 -1.0169 0.02696 0.01953 -0.0235 1.0000 0.0411
-10.500 -0.9991 0.02602 0.01854 -0.0222 1.0000 0.0417
-10.250 -0.9804 0.02513 0.01758 -0.0210 1.0000 0.0425
-10.000 -0.9610 0.02428 0.01666 -0.0198 1.0000 0.0433
-9.750 -0.9410 0.02346 0.01575 -0.0186 1.0000 0.0443
-9.500 -0.9203 0.02267 0.01484 -0.0175 1.0000 0.0453
-9.250 -0.9002 0.02188 0.01406 -0.0163 1.0000 0.0463
-9.000 -0.8790 0.02118 0.01334 -0.0152 1.0000 0.0474
-8.750 -0.8573 0.02051 0.01262 -0.0141 1.0000 0.0487
-8.500 -0.8352 0.01987 0.01191 -0.0130 1.0000 0.0502
-8.250 -0.8131 0.01923 0.01127 -0.0120 1.0000 0.0519
-8.000 -0.7906 0.01867 0.01070 -0.0109 1.0000 0.0540
-7.750 -0.7676 0.01813 0.01011 -0.0099 1.0000 0.0570
-7.500 -0.7446 0.01764 0.00967 -0.0089 1.0000 0.0603
-7.250 -0.7212 0.01719 0.00922 -0.0079 1.0000 0.0648
-7.000 -0.6974 0.01680 0.00883 -0.0069 1.0000 0.0702
-6.750 -0.6735 0.01646 0.00852 -0.0060 1.0000 0.0754
-6.500 -0.6495 0.01614 0.00818 -0.0050 1.0000 0.0810
-6.250 -0.6254 0.01587 0.00791 -0.0041 1.0000 0.0863
-6.000 -0.6014 0.01559 0.00762 -0.0031 1.0000 0.0912
-5.750 -0.5774 0.01535 0.00739 -0.0021 1.0000 0.0959
-5.500 -0.5532 0.01511 0.00710 -0.0011 1.0000 0.1004
-5.250 -0.5299 0.01480 0.00686 0.0000 1.0000 0.1043
-5.000 -0.4995 0.01454 0.00659 -0.0004 0.9928 0.1087
-4.750 -0.4584 0.01423 0.00627 -0.0029 0.9664 0.1136
-4.500 -0.4038 0.01396 0.00599 -0.0080 0.8960 0.1215
-4.250 -0.3625 0.01398 0.00562 -0.0099 0.7380 0.1284
-4.000 -0.3401 0.01413 0.00538 -0.0083 0.6459 0.1334
-3.750 -0.3155 0.01414 0.00515 -0.0072 0.6039 0.1381
-3.500 -0.2904 0.01400 0.00492 -0.0064 0.5746 0.1424
-3.250 -0.2650 0.01388 0.00472 -0.0056 0.5496 0.1468
-3.000 -0.2390 0.01378 0.00451 -0.0049 0.5276 0.1518
-2.750 -0.2131 0.01365 0.00432 -0.0043 0.5083 0.1576
-2.500 -0.1870 0.01353 0.00416 -0.0036 0.4912 0.1650
-2.250 -0.1606 0.01341 0.00400 -0.0030 0.4757 0.1732
-2.000 -0.1343 0.01328 0.00385 -0.0024 0.4614 0.1837
-1.750 -0.1082 0.01315 0.00371 -0.0018 0.4478 0.1971
-1.500 -0.0821 0.01300 0.00358 -0.0013 0.4340 0.2152
-1.250 -0.0563 0.01280 0.00348 -0.0007 0.4212 0.2436
-1.000 -0.0311 0.01257 0.00340 0.0000 0.4090 0.2959
-0.750 -0.0059 0.01232 0.00334 0.0007 0.3971 0.3550
-0.500 0.0186 0.01205 0.00330 0.0016 0.3868 0.4237
-0.250 0.0424 0.01177 0.00329 0.0026 0.3764 0.5031
0.000 0.0657 0.01149 0.00332 0.0039 0.3667 0.5881
0.250 0.0894 0.01131 0.00337 0.0052 0.3570 0.6634
0.500 0.1142 0.01119 0.00344 0.0064 0.3477 0.7260
0.750 0.1402 0.01114 0.00352 0.0074 0.3381 0.7851
1.000 0.1711 0.01114 0.00366 0.0076 0.3282 0.8433
1.500 0.2536 0.01144 0.00395 0.0035 0.3090 0.9316
2.000 0.3361 0.01180 0.00417 -0.0011 0.2908 0.9711
2.250 0.3763 0.01198 0.00424 -0.0034 0.2811 0.9828
2.500 0.4204 0.01212 0.00431 -0.0065 0.2708 0.9936
2.750 0.4590 0.01226 0.00437 -0.0086 0.2635 1.0000
3.000 0.4820 0.01239 0.00448 -0.0076 0.2577 1.0000
3.250 0.5051 0.01256 0.00458 -0.0065 0.2525 1.0000
3.500 0.5282 0.01275 0.00471 -0.0054 0.2480 1.0000
3.750 0.5519 0.01290 0.00488 -0.0045 0.2429 1.0000
4.000 0.5755 0.01309 0.00503 -0.0035 0.2376 1.0000
4.500 0.6229 0.01351 0.00540 -0.0015 0.2280 1.0000
4.750 0.6468 0.01372 0.00561 -0.0006 0.2231 1.0000
5.000 0.6704 0.01397 0.00581 0.0004 0.2181 1.0000
5.250 0.6945 0.01421 0.00605 0.0013 0.2131 1.0000
5.500 0.7187 0.01442 0.00629 0.0021 0.2073 1.0000
5.750 0.7423 0.01469 0.00653 0.0031 0.2019 1.0000
6.000 0.7664 0.01495 0.00681 0.0039 0.1967 1.0000
6.250 0.7905 0.01519 0.00709 0.0048 0.1906 1.0000
6.500 0.8139 0.01550 0.00735 0.0057 0.1849 1.0000
6.750 0.8384 0.01574 0.00767 0.0065 0.1781 1.0000
7.000 0.8620 0.01604 0.00795 0.0073 0.1717 1.0000
7.250 0.8860 0.01635 0.00831 0.0082 0.1656 1.0000
7.500 0.9095 0.01668 0.00864 0.0090 0.1592 1.0000
7.750 0.9330 0.01705 0.00901 0.0098 0.1535 1.0000
8.000 0.9562 0.01743 0.00941 0.0106 0.1479 1.0000
8.250 0.9788 0.01787 0.00983 0.0115 0.1433 1.0000
8.500 1.0018 0.01830 0.01031 0.0123 0.1383 1.0000
8.750 1.0237 0.01879 0.01078 0.0132 0.1330 1.0000
9.000 1.0460 0.01927 0.01130 0.0141 0.1278 1.0000
9.250 1.0675 0.01980 0.01183 0.0149 0.1228 1.0000
9.500 1.0880 0.02040 0.01243 0.0159 0.1190 1.0000
9.750 1.1096 0.02093 0.01305 0.0168 0.1155 1.0000
10.000 1.1301 0.02152 0.01369 0.0177 0.1122 1.0000
10.250 1.1490 0.02222 0.01438 0.0188 0.1091 1.0000
10.500 1.1686 0.02286 0.01511 0.0198 0.1063 1.0000
10.750 1.1880 0.02349 0.01584 0.0209 0.1032 1.0000
11.000 1.2058 0.02420 0.01661 0.0220 0.1004 1.0000
11.250 1.2213 0.02504 0.01745 0.0233 0.0979 1.0000
11.500 1.2381 0.02578 0.01831 0.0245 0.0952 1.0000
11.750 1.2537 0.02656 0.01920 0.0257 0.0923 1.0000
12.000 1.2665 0.02743 0.02014 0.0272 0.0895 1.0000
12.250 1.2750 0.02847 0.02120 0.0290 0.0873 1.0000
12.500 1.2836 0.02941 0.02229 0.0309 0.0848 1.0000
12.750 1.2889 0.03055 0.02354 0.0328 0.0824 1.0000
13.000 1.2913 0.03199 0.02505 0.0343 0.0803 1.0000
13.250 1.2902 0.03391 0.02703 0.0352 0.0786 1.0000
13.500 1.2901 0.03614 0.02940 0.0352 0.0767 1.0000
13.750 1.2886 0.03891 0.03233 0.0343 0.0747 1.0000
14.000 1.2846 0.04236 0.03589 0.0326 0.0728 1.0000
14.250 1.2777 0.04635 0.03998 0.0305 0.0713 1.0000
14.500 1.2679 0.05076 0.04444 0.0281 0.0700 1.0000
14.750 1.2592 0.05512 0.04896 0.0260 0.0684 1.0000
15.000 1.2475 0.05990 0.05388 0.0235 0.0668 1.0000
15.250 1.2337 0.06504 0.05912 0.0209 0.0654 1.0000
15.500 1.2194 0.07030 0.06447 0.0182 0.0643 1.0000
15.750 1.2050 0.07564 0.06987 0.0154 0.0632 1.0000
16.000 1.1916 0.08094 0.07522 0.0127 0.0621 1.0000
16.250 1.1760 0.08699 0.08142 0.0095 0.0607 1.0000
16.500 1.1618 0.09297 0.08752 0.0063 0.0595 1.0000
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