GOE 8K AIRFOIL (goe08k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 8K AIRFOIL (goe08k-il) Reynolds number: 1,000,000 Max Cl/Cd: 143.1 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe08k-il-1000000.txt Download as CSV file: xf-goe08k-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 8K 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.3615 0.03654 0.03407 -0.2187 0.9434 0.0127
-13.750 -0.3990 0.03116 0.02844 -0.2195 0.9349 0.0130
-13.500 -0.3994 0.02761 0.02461 -0.2221 0.9325 0.0131
-13.250 -0.3870 0.02489 0.02161 -0.2246 0.9308 0.0133
-13.000 -0.4043 0.02416 0.02077 -0.2174 0.9237 0.0134
-12.750 -0.3918 0.02272 0.01914 -0.2170 0.9212 0.0136
-12.500 -0.3710 0.02147 0.01770 -0.2178 0.9193 0.0139
-12.250 -0.3681 0.02060 0.01668 -0.2142 0.9155 0.0140
-12.000 -0.3861 0.01946 0.01536 -0.2063 0.9098 0.0143
-11.750 -0.3717 0.01830 0.01406 -0.2050 0.9072 0.0148
-11.500 -0.3430 0.01762 0.01329 -0.2064 0.9056 0.0153
-11.250 -0.3115 0.01698 0.01255 -0.2084 0.9040 0.0160
-11.000 -0.3319 0.01685 0.01238 -0.1983 0.8987 0.0159
-10.750 -0.3168 0.01631 0.01174 -0.1963 0.8960 0.0165
-10.500 -0.2966 0.01573 0.01103 -0.1955 0.8939 0.0169
-10.250 -0.2694 0.01510 0.01025 -0.1962 0.8921 0.0175
-10.000 -0.2399 0.01425 0.00929 -0.1976 0.8904 0.0184
-9.750 -0.2536 0.01420 0.00924 -0.1887 0.8858 0.0188
-9.500 -0.2423 0.01385 0.00882 -0.1855 0.8827 0.0192
-9.250 -0.2198 0.01353 0.00844 -0.1848 0.8806 0.0201
-9.000 -0.1944 0.01317 0.00798 -0.1848 0.8787 0.0209
-8.750 -0.1649 0.01261 0.00732 -0.1858 0.8771 0.0220
-8.500 -0.1303 0.01237 0.00706 -0.1879 0.8755 0.0232
-8.250 -0.1512 0.01236 0.00704 -0.1771 0.8706 0.0235
-8.000 -0.1336 0.01219 0.00684 -0.1751 0.8680 0.0244
-7.750 -0.1092 0.01201 0.00658 -0.1747 0.8659 0.0254
-7.500 -0.0837 0.01164 0.00618 -0.1746 0.8639 0.0271
-7.250 -0.0466 0.01158 0.00610 -0.1770 0.8623 0.0288
-7.000 -0.0374 0.01161 0.00612 -0.1730 0.8591 0.0300
-6.750 -0.0326 0.01153 0.00600 -0.1680 0.8554 0.0305
-6.500 -0.0140 0.01130 0.00574 -0.1663 0.8527 0.0320
-6.250 0.0121 0.01134 0.00578 -0.1661 0.8506 0.0333
-6.000 0.0441 0.01135 0.00577 -0.1674 0.8489 0.0348
-5.750 0.0818 0.01137 0.00574 -0.1699 0.8472 0.0364
-5.500 0.0759 0.01143 0.00578 -0.1624 0.8430 0.0367
-5.250 0.0867 0.01109 0.00541 -0.1589 0.8396 0.0383
-5.000 0.1082 0.01101 0.00533 -0.1577 0.8370 0.0393
-4.750 0.1366 0.01091 0.00520 -0.1581 0.8350 0.0405
-4.500 0.1724 0.01085 0.00509 -0.1603 0.8332 0.0423
-4.250 0.1737 0.01090 0.00514 -0.1544 0.8292 0.0431
-4.000 0.1869 0.01085 0.00505 -0.1513 0.8257 0.0438
-3.750 0.2072 0.01071 0.00487 -0.1498 0.8229 0.0448
-3.500 0.2320 0.01022 0.00438 -0.1495 0.8206 0.0468
-3.250 0.2659 0.01006 0.00420 -0.1513 0.8187 0.0483
-3.000 0.2710 0.01009 0.00423 -0.1463 0.8150 0.0494
-2.750 0.2830 0.00998 0.00411 -0.1429 0.8115 0.0502
-2.500 0.3020 0.00986 0.00397 -0.1412 0.8087 0.0513
-2.250 0.3291 0.00975 0.00383 -0.1412 0.8066 0.0525
-2.000 0.3626 0.00963 0.00368 -0.1429 0.8047 0.0534
-1.750 0.3728 0.00956 0.00360 -0.1391 0.8015 0.0542
-1.500 0.3824 0.00937 0.00340 -0.1351 0.7981 0.0551
-1.250 0.4002 0.00921 0.00322 -0.1331 0.7953 0.0563
-1.000 0.4239 0.00908 0.00307 -0.1324 0.7930 0.0576
-0.750 0.4543 0.00896 0.00294 -0.1333 0.7910 0.0590
-0.500 0.4825 0.00889 0.00285 -0.1337 0.7889 0.0606
-0.250 0.4915 0.00892 0.00289 -0.1296 0.7859 0.0618
0.000 0.5097 0.00890 0.00287 -0.1277 0.7833 0.0625
0.250 0.5313 0.00888 0.00284 -0.1266 0.7810 0.0639
0.500 0.5562 0.00885 0.00281 -0.1262 0.7790 0.0649
0.750 0.5876 0.00875 0.00269 -0.1273 0.7768 0.0686
1.000 0.6150 0.00873 0.00266 -0.1274 0.7742 0.0715
1.250 0.6193 0.00879 0.00276 -0.1223 0.7703 0.0756
1.500 0.6381 0.00879 0.00279 -0.1206 0.7671 0.0883
1.750 0.9463 0.00759 0.00399 -0.1875 0.7748 0.9899
2.000 1.0059 0.00770 0.00411 -0.1952 0.7735 0.9960
2.250 1.0480 0.00770 0.00413 -0.1990 0.7711 0.9994
2.500 1.0691 0.00774 0.00417 -0.1979 0.7681 1.0000
2.750 1.0855 0.00778 0.00421 -0.1957 0.7645 1.0000
3.000 1.1162 0.00780 0.00418 -0.1967 0.7606 1.0000
3.250 1.1067 0.00797 0.00439 -0.1885 0.7542 1.0000
3.500 1.1209 0.00805 0.00444 -0.1857 0.7485 1.0000
3.750 1.1411 0.00813 0.00451 -0.1844 0.7444 1.0000
4.000 1.1441 0.00830 0.00472 -0.1791 0.7384 1.0000
4.250 1.1613 0.00841 0.00479 -0.1770 0.7324 1.0000
4.500 1.1749 0.00855 0.00496 -0.1742 0.7282 1.0000
4.750 1.1809 0.00875 0.00516 -0.1696 0.7197 1.0000
5.000 1.1912 0.00896 0.00537 -0.1660 0.7125 1.0000
5.250 1.2000 0.00920 0.00560 -0.1622 0.7038 1.0000
5.500 1.2078 0.00948 0.00590 -0.1581 0.6937 1.0000
5.750 1.2175 0.00977 0.00617 -0.1545 0.6845 1.0000
6.000 1.2233 0.01016 0.00653 -0.1501 0.6710 1.0000
6.250 1.2271 0.01063 0.00698 -0.1454 0.6549 1.0000
6.500 1.2306 0.01116 0.00748 -0.1406 0.6338 1.0000
6.750 1.2108 0.01242 0.00853 -0.1313 0.5866 1.0000
7.000 1.1865 0.01407 0.00991 -0.1214 0.5358 1.0000
7.250 1.1806 0.01526 0.01095 -0.1154 0.5030 1.0000
7.500 1.1763 0.01646 0.01200 -0.1099 0.4681 1.0000
7.750 1.1718 0.01775 0.01311 -0.1045 0.4306 1.0000
8.000 1.1741 0.01880 0.01404 -0.1004 0.3998 1.0000
8.250 1.1660 0.02039 0.01536 -0.0947 0.3489 1.0000
8.500 1.1566 0.02211 0.01679 -0.0890 0.2897 1.0000
8.750 1.1517 0.02369 0.01808 -0.0842 0.2372 1.0000
9.000 1.1511 0.02510 0.01928 -0.0802 0.1951 1.0000
9.250 1.1542 0.02637 0.02035 -0.0769 0.1576 1.0000
9.500 1.1555 0.02776 0.02152 -0.0734 0.1165 1.0000
9.750 1.1572 0.02918 0.02274 -0.0701 0.0804 1.0000
10.000 1.1643 0.03033 0.02380 -0.0676 0.0629 1.0000
10.250 1.1734 0.03138 0.02478 -0.0654 0.0467 1.0000
10.500 1.1823 0.03245 0.02577 -0.0632 0.0349 1.0000
10.750 1.1924 0.03346 0.02675 -0.0613 0.0291 1.0000
11.000 1.2046 0.03436 0.02767 -0.0596 0.0261 1.0000
11.250 1.2165 0.03529 0.02861 -0.0580 0.0242 1.0000
11.500 1.2267 0.03635 0.02970 -0.0562 0.0227 1.0000
11.750 1.2382 0.03734 0.03074 -0.0545 0.0216 1.0000
12.000 1.2510 0.03824 0.03167 -0.0531 0.0205 1.0000
12.250 1.2617 0.03929 0.03275 -0.0516 0.0192 1.0000
12.500 1.2713 0.04044 0.03393 -0.0498 0.0184 1.0000
12.750 1.2771 0.04189 0.03544 -0.0477 0.0173 1.0000
13.000 1.2890 0.04291 0.03651 -0.0463 0.0166 1.0000
13.250 1.2995 0.04403 0.03768 -0.0449 0.0160 1.0000
13.500 1.3105 0.04513 0.03880 -0.0436 0.0153 1.0000
13.750 1.3185 0.04648 0.04021 -0.0420 0.0149 1.0000
14.000 1.3260 0.04788 0.04165 -0.0403 0.0143 1.0000
14.250 1.3284 0.04972 0.04355 -0.0383 0.0137 1.0000
14.500 1.3351 0.05124 0.04514 -0.0367 0.0134 1.0000
14.750 1.3457 0.05244 0.04640 -0.0355 0.0129 1.0000
15.000 1.3545 0.05381 0.04782 -0.0343 0.0125 1.0000
15.250 1.3613 0.05537 0.04943 -0.0329 0.0121 1.0000
15.500 1.3684 0.05692 0.05104 -0.0316 0.0118 1.0000
15.750 1.3733 0.05869 0.05286 -0.0302 0.0114 1.0000
16.000 1.3738 0.06088 0.05511 -0.0286 0.0110 1.0000
16.250 1.3701 0.06351 0.05782 -0.0267 0.0106 1.0000
16.500 1.3745 0.06543 0.05982 -0.0255 0.0105 1.0000
16.750 1.3824 0.06702 0.06147 -0.0246 0.0103 1.0000
17.000 1.3849 0.06918 0.06371 -0.0234 0.0101 1.0000
17.250 1.3863 0.07146 0.06609 -0.0223 0.0100 1.0000
17.500 1.3928 0.07327 0.06796 -0.0216 0.0095 1.0000
17.750 1.3946 0.07556 0.07032 -0.0207 0.0095 1.0000
18.000 1.3936 0.07819 0.07304 -0.0197 0.0093 1.0000
18.250 1.3971 0.08039 0.07531 -0.0191 0.0092 1.0000
18.500 1.4016 0.08251 0.07745 -0.0187 0.0087 1.0000
18.750 1.3989 0.08547 0.08051 -0.0180 0.0088 1.0000
19.000 1.3954 0.08857 0.08369 -0.0175 0.0086 1.0000
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Polar data table (+)
Polar graphs
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