GOE 769 AIRFOIL (goe769-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 769 AIRFOIL (goe769-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.88 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe769-il-1000000.txt Download as CSV file: xf-goe769-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3110 0.11095 0.10920 -0.0187 1.0000 0.0289
-10.750 -0.3016 0.10873 0.10700 -0.0189 1.0000 0.0291
-10.500 -0.6839 0.03030 0.02751 -0.0725 0.9923 0.0271
-10.250 -0.6591 0.02662 0.02348 -0.0762 0.9769 0.0273
-10.000 -0.6182 0.02373 0.02026 -0.0816 0.9537 0.0275
-9.750 -0.5845 0.02195 0.01811 -0.0841 0.8947 0.0277
-9.500 -0.5683 0.02096 0.01675 -0.0823 0.8361 0.0278
-9.250 -0.5500 0.02008 0.01559 -0.0808 0.7961 0.0280
-9.000 -0.5294 0.01927 0.01455 -0.0796 0.7670 0.0282
-8.750 -0.5077 0.01851 0.01357 -0.0786 0.7439 0.0283
-8.500 -0.4848 0.01784 0.01272 -0.0776 0.7247 0.0284
-8.250 -0.4609 0.01728 0.01199 -0.0768 0.7084 0.0286
-7.750 -0.4130 0.01585 0.01026 -0.0752 0.6827 0.0289
-7.500 -0.3897 0.01494 0.00923 -0.0743 0.6717 0.0293
-7.250 -0.3643 0.01438 0.00861 -0.0737 0.6618 0.0296
-7.000 -0.3386 0.01398 0.00813 -0.0730 0.6513 0.0298
-6.750 -0.3120 0.01361 0.00772 -0.0725 0.6423 0.0301
-6.500 -0.2854 0.01334 0.00737 -0.0719 0.6330 0.0305
-6.250 -0.2584 0.01301 0.00699 -0.0714 0.6253 0.0309
-6.000 -0.2316 0.01268 0.00658 -0.0708 0.6168 0.0313
-5.750 -0.2047 0.01236 0.00620 -0.0702 0.6087 0.0316
-5.500 -0.1774 0.01205 0.00583 -0.0697 0.6002 0.0319
-5.250 -0.1504 0.01182 0.00552 -0.0692 0.5908 0.0322
-5.000 -0.1227 0.01157 0.00522 -0.0687 0.5826 0.0324
-4.750 -0.0963 0.01114 0.00472 -0.0681 0.5731 0.0329
-4.500 -0.0693 0.01081 0.00436 -0.0676 0.5630 0.0335
-4.250 -0.0421 0.01062 0.00411 -0.0670 0.5496 0.0340
-4.000 -0.0146 0.01044 0.00389 -0.0666 0.5353 0.0346
-3.750 0.0131 0.01029 0.00368 -0.0661 0.5222 0.0352
-3.500 0.0406 0.01016 0.00348 -0.0656 0.5091 0.0359
-3.250 0.0684 0.01007 0.00332 -0.0652 0.4952 0.0365
-3.000 0.0955 0.00985 0.00305 -0.0647 0.4814 0.0375
-2.750 0.1230 0.00975 0.00291 -0.0642 0.4680 0.0387
-2.250 0.1784 0.00960 0.00265 -0.0633 0.4437 0.0415
-2.000 0.2059 0.00952 0.00253 -0.0629 0.4324 0.0435
-1.750 0.2337 0.00946 0.00244 -0.0624 0.4217 0.0458
-1.500 0.2614 0.00938 0.00235 -0.0620 0.4129 0.0498
-1.250 0.2891 0.00932 0.00228 -0.0616 0.4039 0.0559
-1.000 0.3167 0.00926 0.00224 -0.0612 0.3955 0.0651
-0.750 0.3446 0.00923 0.00222 -0.0608 0.3870 0.0746
-0.500 0.3723 0.00925 0.00222 -0.0605 0.3789 0.0831
-0.250 0.4005 0.00923 0.00222 -0.0602 0.3724 0.0908
0.000 0.4282 0.00925 0.00223 -0.0598 0.3647 0.0975
0.250 0.4563 0.00928 0.00224 -0.0595 0.3581 0.1034
0.500 0.4841 0.00927 0.00224 -0.0591 0.3510 0.1113
0.750 0.5116 0.00932 0.00226 -0.0587 0.3433 0.1188
1.000 0.5397 0.00931 0.00228 -0.0584 0.3380 0.1275
1.250 0.5672 0.00932 0.00230 -0.0581 0.3312 0.1394
1.500 0.5946 0.00934 0.00234 -0.0577 0.3243 0.1581
1.750 0.6218 0.00924 0.00239 -0.0573 0.3178 0.2068
2.000 0.6480 0.00915 0.00247 -0.0569 0.3101 0.2911
2.250 0.6735 0.00888 0.00255 -0.0563 0.3044 0.4303
2.500 0.6862 0.00783 0.00270 -0.0531 0.2984 0.8609
2.750 0.7715 0.00790 0.00283 -0.0649 0.2853 1.0000
3.000 0.7963 0.00807 0.00292 -0.0641 0.2766 1.0000
3.250 0.8218 0.00820 0.00300 -0.0633 0.2696 1.0000
3.500 0.8467 0.00839 0.00311 -0.0625 0.2608 1.0000
3.750 0.8720 0.00855 0.00321 -0.0617 0.2534 1.0000
4.000 0.8968 0.00875 0.00334 -0.0609 0.2454 1.0000
4.250 0.9220 0.00892 0.00346 -0.0602 0.2392 1.0000
4.500 0.9471 0.00911 0.00359 -0.0594 0.2334 1.0000
4.750 0.9716 0.00934 0.00376 -0.0586 0.2270 1.0000
5.000 0.9971 0.00949 0.00389 -0.0579 0.2232 1.0000
5.250 1.0221 0.00969 0.00405 -0.0572 0.2185 1.0000
5.500 1.0465 0.00994 0.00424 -0.0564 0.2136 1.0000
5.750 1.0719 0.01010 0.00440 -0.0558 0.2106 1.0000
6.000 1.0972 0.01027 0.00455 -0.0551 0.2076 1.0000
6.250 1.1221 0.01048 0.00473 -0.0544 0.2041 1.0000
6.500 1.1463 0.01074 0.00495 -0.0537 0.2000 1.0000
6.750 1.1709 0.01096 0.00516 -0.0530 0.1969 1.0000
7.000 1.1964 0.01112 0.00532 -0.0524 0.1948 1.0000
7.250 1.2212 0.01132 0.00551 -0.0518 0.1922 1.0000
7.500 1.2456 0.01155 0.00573 -0.0511 0.1894 1.0000
7.750 1.2691 0.01184 0.00598 -0.0503 0.1860 1.0000
8.000 1.2926 0.01211 0.00625 -0.0495 0.1831 1.0000
8.250 1.3176 0.01228 0.00643 -0.0489 0.1814 1.0000
8.500 1.3419 0.01249 0.00665 -0.0482 0.1791 1.0000
8.750 1.3655 0.01273 0.00689 -0.0475 0.1767 1.0000
9.000 1.3882 0.01303 0.00716 -0.0466 0.1741 1.0000
9.250 1.4093 0.01340 0.00751 -0.0455 0.1709 1.0000
9.500 1.4325 0.01363 0.00777 -0.0447 0.1693 1.0000
9.750 1.4559 0.01385 0.00801 -0.0440 0.1676 1.0000
10.000 1.4783 0.01410 0.00827 -0.0431 0.1655 1.0000
10.250 1.4996 0.01440 0.00857 -0.0421 0.1632 1.0000
10.500 1.5196 0.01475 0.00892 -0.0409 0.1609 1.0000
10.750 1.5369 0.01521 0.00937 -0.0394 0.1581 1.0000
11.000 1.5568 0.01551 0.00970 -0.0381 0.1568 1.0000
11.250 1.5755 0.01578 0.01000 -0.0367 0.1554 1.0000
11.500 1.5921 0.01609 0.01034 -0.0349 0.1538 1.0000
11.750 1.6075 0.01645 0.01072 -0.0330 0.1520 1.0000
12.000 1.6217 0.01689 0.01117 -0.0311 0.1501 1.0000
12.250 1.6339 0.01744 0.01173 -0.0290 0.1480 1.0000
12.500 1.6423 0.01819 0.01250 -0.0266 0.1456 1.0000
12.750 1.6586 0.01863 0.01299 -0.0253 0.1447 1.0000
13.000 1.6738 0.01916 0.01357 -0.0240 0.1436 1.0000
13.250 1.6878 0.01978 0.01424 -0.0227 0.1422 1.0000
13.500 1.7006 0.02052 0.01501 -0.0214 0.1407 1.0000
13.750 1.7121 0.02139 0.01591 -0.0202 0.1390 1.0000
14.000 1.7212 0.02250 0.01704 -0.0190 0.1369 1.0000
14.250 1.7262 0.02401 0.01858 -0.0178 0.1347 1.0000
14.500 1.7388 0.02505 0.01968 -0.0172 0.1335 1.0000
14.750 1.7520 0.02608 0.02077 -0.0167 0.1321 1.0000
15.000 1.7629 0.02736 0.02210 -0.0163 0.1307 1.0000
15.250 1.7721 0.02882 0.02361 -0.0159 0.1291 1.0000
15.500 1.7788 0.03058 0.02541 -0.0157 0.1276 1.0000
15.750 1.7828 0.03262 0.02750 -0.0155 0.1262 1.0000
16.000 1.7811 0.03527 0.03019 -0.0153 0.1242 1.0000
16.250 1.7850 0.03737 0.03236 -0.0153 0.1232 1.0000
16.500 1.7916 0.03922 0.03429 -0.0152 0.1223 1.0000
16.750 1.7968 0.04124 0.03637 -0.0152 0.1212 1.0000
17.000 1.7987 0.04358 0.03879 -0.0152 0.1199 1.0000
17.250 1.7981 0.04621 0.04148 -0.0153 0.1188 1.0000
17.500 1.7951 0.04918 0.04451 -0.0156 0.1174 1.0000
17.750 1.7885 0.05261 0.04799 -0.0160 0.1160 1.0000
18.000 1.7795 0.05635 0.05180 -0.0166 0.1148 1.0000
18.250 1.7714 0.06006 0.05557 -0.0172 0.1134 1.0000
18.500 1.7705 0.06298 0.05858 -0.0177 0.1128 1.0000
18.750 1.7697 0.06593 0.06161 -0.0183 0.1116 1.0000
19.000 1.7652 0.06937 0.06514 -0.0190 0.1105 1.0000
19.250 1.7585 0.07310 0.06893 -0.0199 0.1094 1.0000
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