GOE 769 AIRFOIL (goe769-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 769 AIRFOIL (goe769-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.95 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe769-il-1000000-n5.txt Download as CSV file: xf-goe769-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 769 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.9447 0.03339 0.03020 -0.0816 1.0000 0.0220
-13.250 -0.9455 0.03065 0.02729 -0.0811 1.0000 0.0220
-13.000 -0.9389 0.02874 0.02524 -0.0801 1.0000 0.0220
-12.750 -0.9291 0.02714 0.02352 -0.0788 1.0000 0.0221
-12.500 -0.9166 0.02580 0.02207 -0.0775 1.0000 0.0221
-12.250 -0.8958 0.02449 0.02064 -0.0775 0.9965 0.0222
-12.000 -0.8690 0.02329 0.01933 -0.0784 0.9841 0.0223
-11.750 -0.8299 0.02204 0.01796 -0.0816 0.9684 0.0223
-11.500 -0.7819 0.02051 0.01622 -0.0868 0.9206 0.0225
-11.250 -0.7633 0.01983 0.01519 -0.0853 0.8404 0.0226
-11.000 -0.7452 0.01921 0.01433 -0.0837 0.7902 0.0227
-10.750 -0.7245 0.01864 0.01358 -0.0825 0.7572 0.0228
-10.500 -0.7024 0.01810 0.01289 -0.0815 0.7321 0.0229
-10.250 -0.6794 0.01757 0.01224 -0.0806 0.7123 0.0230
-10.000 -0.6556 0.01709 0.01165 -0.0798 0.6951 0.0232
-9.750 -0.6311 0.01664 0.01110 -0.0790 0.6800 0.0233
-9.500 -0.6064 0.01621 0.01057 -0.0783 0.6670 0.0234
-9.250 -0.5813 0.01580 0.01007 -0.0776 0.6543 0.0236
-9.000 -0.5559 0.01539 0.00958 -0.0770 0.6446 0.0237
-8.750 -0.5302 0.01502 0.00912 -0.0763 0.6346 0.0239
-8.500 -0.5043 0.01464 0.00867 -0.0757 0.6266 0.0240
-8.250 -0.4780 0.01429 0.00825 -0.0751 0.6178 0.0242
-8.000 -0.4517 0.01398 0.00787 -0.0745 0.6093 0.0244
-7.750 -0.4250 0.01366 0.00749 -0.0740 0.6021 0.0246
-7.500 -0.3982 0.01336 0.00712 -0.0734 0.5944 0.0248
-7.250 -0.3714 0.01307 0.00676 -0.0729 0.5875 0.0250
-7.000 -0.3444 0.01278 0.00642 -0.0724 0.5798 0.0252
-6.750 -0.3174 0.01253 0.00609 -0.0718 0.5707 0.0253
-6.500 -0.2901 0.01227 0.00578 -0.0713 0.5626 0.0254
-6.250 -0.2628 0.01206 0.00550 -0.0708 0.5531 0.0256
-6.000 -0.2358 0.01175 0.00515 -0.0703 0.5450 0.0258
-5.750 -0.2086 0.01148 0.00483 -0.0698 0.5353 0.0261
-5.500 -0.1813 0.01126 0.00456 -0.0693 0.5260 0.0264
-5.250 -0.1538 0.01108 0.00433 -0.0689 0.5145 0.0267
-5.000 -0.1262 0.01092 0.00411 -0.0684 0.5024 0.0270
-4.750 -0.0987 0.01079 0.00391 -0.0679 0.4880 0.0273
-4.500 -0.0713 0.01068 0.00373 -0.0674 0.4721 0.0277
-4.250 -0.0439 0.01059 0.00356 -0.0670 0.4549 0.0280
-4.000 -0.0164 0.01051 0.00339 -0.0665 0.4386 0.0284
-3.750 0.0113 0.01043 0.00325 -0.0660 0.4253 0.0288
-3.500 0.0390 0.01036 0.00312 -0.0656 0.4146 0.0291
-3.250 0.0668 0.01022 0.00296 -0.0652 0.4063 0.0297
-3.000 0.0945 0.01014 0.00284 -0.0648 0.3968 0.0303
-2.750 0.1226 0.01006 0.00273 -0.0644 0.3889 0.0311
-2.500 0.1504 0.01002 0.00264 -0.0640 0.3798 0.0319
-2.250 0.1785 0.00995 0.00255 -0.0636 0.3736 0.0328
-2.000 0.2064 0.00988 0.00246 -0.0632 0.3658 0.0339
-1.750 0.2342 0.00984 0.00240 -0.0628 0.3584 0.0354
-1.500 0.2623 0.00980 0.00233 -0.0625 0.3516 0.0371
-1.250 0.2901 0.00976 0.00228 -0.0621 0.3447 0.0398
-1.000 0.3181 0.00972 0.00224 -0.0617 0.3391 0.0437
-0.750 0.3460 0.00968 0.00221 -0.0614 0.3326 0.0493
-0.500 0.3737 0.00968 0.00219 -0.0610 0.3252 0.0561
-0.250 0.4016 0.00965 0.00218 -0.0607 0.3195 0.0641
0.000 0.4296 0.00964 0.00219 -0.0603 0.3137 0.0719
0.250 0.4573 0.00967 0.00220 -0.0600 0.3072 0.0789
0.500 0.4853 0.00968 0.00222 -0.0597 0.3016 0.0852
0.750 0.5130 0.00971 0.00225 -0.0593 0.2939 0.0916
1.000 0.5406 0.00977 0.00228 -0.0589 0.2872 0.0975
1.250 0.5685 0.00980 0.00232 -0.0586 0.2808 0.1041
1.500 0.5958 0.00986 0.00237 -0.0582 0.2731 0.1139
1.750 0.6233 0.00989 0.00242 -0.0579 0.2661 0.1251
2.000 0.6504 0.00998 0.00249 -0.0575 0.2569 0.1375
2.250 0.6776 0.01003 0.00256 -0.0571 0.2492 0.1556
2.500 0.7043 0.01009 0.00264 -0.0567 0.2414 0.1832
2.750 0.7311 0.01008 0.00274 -0.0563 0.2357 0.2354
3.000 0.7574 0.01010 0.00286 -0.0558 0.2289 0.2892
3.250 0.7835 0.01009 0.00298 -0.0553 0.2232 0.3572
3.500 0.8069 0.00973 0.00313 -0.0545 0.2188 0.5708
4.000 0.8948 0.00922 0.00351 -0.0610 0.2082 1.0000
4.250 0.9203 0.00936 0.00362 -0.0603 0.2049 1.0000
4.500 0.9455 0.00953 0.00375 -0.0596 0.2012 1.0000
4.750 0.9706 0.00972 0.00389 -0.0588 0.1978 1.0000
5.000 0.9958 0.00990 0.00404 -0.0581 0.1946 1.0000
5.250 1.0214 0.01004 0.00417 -0.0575 0.1923 1.0000
5.500 1.0468 0.01021 0.00431 -0.0568 0.1895 1.0000
5.750 1.0719 0.01040 0.00447 -0.0561 0.1863 1.0000
6.000 1.0968 0.01060 0.00464 -0.0554 0.1834 1.0000
6.250 1.1217 0.01081 0.00482 -0.0548 0.1806 1.0000
6.500 1.1472 0.01097 0.00498 -0.0542 0.1789 1.0000
6.750 1.1723 0.01115 0.00515 -0.0536 0.1765 1.0000
7.000 1.1971 0.01135 0.00534 -0.0529 0.1738 1.0000
7.250 1.2215 0.01158 0.00554 -0.0522 0.1710 1.0000
7.500 1.2457 0.01183 0.00576 -0.0515 0.1683 1.0000
7.750 1.2704 0.01203 0.00597 -0.0508 0.1665 1.0000
8.000 1.2949 0.01223 0.00617 -0.0502 0.1649 1.0000
8.250 1.3191 0.01245 0.00638 -0.0495 0.1627 1.0000
8.500 1.3429 0.01269 0.00662 -0.0488 0.1604 1.0000
8.750 1.3660 0.01296 0.00687 -0.0480 0.1578 1.0000
9.000 1.3886 0.01325 0.00715 -0.0471 0.1551 1.0000
9.250 1.4120 0.01348 0.00739 -0.0463 0.1538 1.0000
9.500 1.4350 0.01372 0.00765 -0.0455 0.1522 1.0000
9.750 1.4575 0.01398 0.00792 -0.0446 0.1504 1.0000
10.000 1.4792 0.01427 0.00821 -0.0437 0.1485 1.0000
10.250 1.5001 0.01459 0.00852 -0.0426 0.1463 1.0000
10.500 1.5200 0.01494 0.00887 -0.0414 0.1441 1.0000
10.750 1.5401 0.01525 0.00920 -0.0402 0.1424 1.0000
11.000 1.5598 0.01555 0.00952 -0.0390 0.1410 1.0000
11.250 1.5768 0.01586 0.00986 -0.0373 0.1395 1.0000
11.500 1.5923 0.01621 0.01023 -0.0353 0.1379 1.0000
11.750 1.6071 0.01661 0.01064 -0.0334 0.1363 1.0000
12.000 1.6211 0.01706 0.01111 -0.0315 0.1347 1.0000
12.250 1.6344 0.01758 0.01164 -0.0296 0.1329 1.0000
12.500 1.6482 0.01810 0.01219 -0.0278 0.1315 1.0000
12.750 1.6627 0.01862 0.01276 -0.0263 0.1303 1.0000
13.000 1.6765 0.01921 0.01339 -0.0249 0.1292 1.0000
13.250 1.6893 0.01990 0.01411 -0.0234 0.1276 1.0000
13.500 1.7009 0.02072 0.01495 -0.0221 0.1258 1.0000
13.750 1.7114 0.02167 0.01593 -0.0208 0.1241 1.0000
14.000 1.7211 0.02277 0.01706 -0.0197 0.1224 1.0000
14.250 1.7314 0.02390 0.01824 -0.0189 0.1208 1.0000
14.500 1.7427 0.02503 0.01942 -0.0182 0.1194 1.0000
14.750 1.7528 0.02633 0.02077 -0.0176 0.1181 1.0000
15.000 1.7612 0.02783 0.02231 -0.0172 0.1163 1.0000
15.250 1.7683 0.02951 0.02404 -0.0168 0.1148 1.0000
15.500 1.7736 0.03142 0.02600 -0.0166 0.1133 1.0000
15.750 1.7767 0.03358 0.02821 -0.0164 0.1115 1.0000
16.000 1.7830 0.03547 0.03017 -0.0163 0.1108 1.0000
16.250 1.7876 0.03752 0.03229 -0.0163 0.1096 1.0000
16.500 1.7903 0.03978 0.03462 -0.0162 0.1085 1.0000
16.750 1.7908 0.04228 0.03718 -0.0163 0.1073 1.0000
17.000 1.7890 0.04504 0.04000 -0.0164 0.1061 1.0000
17.250 1.7850 0.04809 0.04311 -0.0166 0.1049 1.0000
17.500 1.7789 0.05146 0.04655 -0.0170 0.1036 1.0000
17.750 1.7713 0.05506 0.05023 -0.0175 0.1025 1.0000
18.000 1.7683 0.05821 0.05345 -0.0180 0.1013 1.0000
18.250 1.7639 0.06155 0.05688 -0.0186 0.1006 1.0000
18.500 1.7570 0.06523 0.06063 -0.0193 0.0992 1.0000
18.750 1.7488 0.06913 0.06461 -0.0201 0.0982 1.0000
19.000 1.7378 0.07344 0.06900 -0.0212 0.0970 1.0000
19.250 1.7249 0.07803 0.07366 -0.0223 0.0958 1.0000
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Polar data table (+)
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