GOE 7K AIRFOIL (goe07k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 7K AIRFOIL (goe07k-il) Reynolds number: 1,000,000 Max Cl/Cd: 159.87 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe07k-il-1000000.txt Download as CSV file: xf-goe07k-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 7K 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1894 0.11004 0.10814 -0.1104 0.9752 0.0126
-11.500 -0.1796 0.10619 0.10429 -0.1133 0.9749 0.0126
-10.500 -0.1679 0.08938 0.08750 -0.1212 0.9656 0.0129
-10.250 -0.1599 0.08499 0.08312 -0.1247 0.9648 0.0130
-10.000 -0.1453 0.08249 0.08061 -0.1274 0.9642 0.0133
-9.750 -0.1316 0.07949 0.07760 -0.1305 0.9637 0.0138
-9.500 -0.1327 0.07715 0.07529 -0.1299 0.9581 0.0141
-9.250 -0.1264 0.07330 0.07143 -0.1330 0.9558 0.0145
-9.000 -0.1191 0.06885 0.06700 -0.1375 0.9541 0.0151
-8.750 -0.3162 0.02241 0.01916 -0.1472 0.9308 0.0106
-8.500 -0.3038 0.01916 0.01546 -0.1460 0.9283 0.0109
-8.250 -0.2796 0.01720 0.01316 -0.1465 0.9269 0.0112
-8.000 -0.2487 0.01602 0.01177 -0.1481 0.9259 0.0118
-7.750 -0.2440 0.01519 0.01077 -0.1434 0.9208 0.0121
-7.500 -0.2195 0.01457 0.01001 -0.1431 0.9183 0.0125
-7.250 -0.1923 0.01373 0.00899 -0.1434 0.9164 0.0127
-7.000 -0.1656 0.01231 0.00735 -0.1440 0.9146 0.0141
-6.750 -0.1296 0.01182 0.00678 -0.1463 0.9135 0.0148
-6.500 -0.0922 0.01143 0.00632 -0.1489 0.9124 0.0159
-6.250 -0.0877 0.01117 0.00600 -0.1438 0.9077 0.0163
-6.000 -0.0632 0.01089 0.00564 -0.1432 0.9051 0.0169
-5.750 -0.0386 0.01004 0.00467 -0.1429 0.9028 0.0184
-5.500 -0.0064 0.00977 0.00437 -0.1442 0.9011 0.0198
-5.250 0.0293 0.00960 0.00417 -0.1463 0.8996 0.0216
-5.000 0.0531 0.00936 0.00386 -0.1457 0.8969 0.0227
-4.750 0.0628 0.00905 0.00353 -0.1416 0.8926 0.0250
-4.500 0.0894 0.00894 0.00342 -0.1416 0.8901 0.0274
-4.250 0.1195 0.00886 0.00332 -0.1423 0.8880 0.0291
-4.000 0.1503 0.00859 0.00304 -0.1432 0.8861 0.0335
-3.750 0.1876 0.00860 0.00305 -0.1457 0.8844 0.0369
-3.500 0.1962 0.00861 0.00306 -0.1413 0.8804 0.0379
-3.250 0.2144 0.00830 0.00274 -0.1393 0.8770 0.0422
-3.000 0.2422 0.00822 0.00265 -0.1395 0.8745 0.0457
-2.750 0.2736 0.00816 0.00257 -0.1405 0.8724 0.0483
-2.500 0.3079 0.00798 0.00235 -0.1423 0.8703 0.0518
-2.250 0.3126 0.00786 0.00223 -0.1370 0.8658 0.0543
-2.000 0.3342 0.00775 0.00211 -0.1357 0.8625 0.0572
-1.750 0.3608 0.00765 0.00199 -0.1356 0.8600 0.0595
-1.500 0.3926 0.00757 0.00188 -0.1367 0.8578 0.0615
-1.250 0.4168 0.00749 0.00179 -0.1361 0.8550 0.0652
-1.000 0.4267 0.00739 0.00172 -0.1320 0.8506 0.0709
-0.750 0.4491 0.00730 0.00165 -0.1309 0.8473 0.0797
-0.500 0.4696 0.00674 0.00162 -0.1297 0.8444 0.2764
-0.250 0.4801 0.00616 0.00166 -0.1262 0.8405 0.5006
0.000 0.4740 0.00565 0.00170 -0.1185 0.8350 0.6892
0.250 0.6668 0.00551 0.00228 -0.1576 0.8421 0.9462
0.500 0.6833 0.00563 0.00242 -0.1549 0.8369 0.9617
0.750 0.7159 0.00580 0.00257 -0.1561 0.8332 0.9736
1.000 0.7674 0.00597 0.00271 -0.1616 0.8292 0.9811
1.250 0.7993 0.00600 0.00275 -0.1626 0.8208 0.9866
1.500 0.8409 0.00603 0.00273 -0.1659 0.8141 0.9895
1.750 0.8679 0.00606 0.00279 -0.1659 0.8071 0.9943
2.000 0.9194 0.00602 0.00273 -0.1715 0.8016 0.9972
2.250 0.9503 0.00596 0.00268 -0.1725 0.7924 1.0000
2.500 0.9558 0.00598 0.00267 -0.1676 0.7818 1.0000
2.750 0.9624 0.00602 0.00268 -0.1629 0.7698 1.0000
3.000 0.9667 0.00610 0.00271 -0.1576 0.7539 1.0000
3.250 0.9730 0.00621 0.00277 -0.1528 0.7378 1.0000
3.500 0.9767 0.00636 0.00285 -0.1474 0.7185 1.0000
3.750 0.9836 0.00653 0.00296 -0.1428 0.6999 1.0000
4.000 0.9809 0.00682 0.00312 -0.1359 0.6647 1.0000
4.250 0.9769 0.00721 0.00335 -0.1289 0.6216 1.0000
4.500 0.9556 0.00805 0.00381 -0.1182 0.5420 1.0000
4.750 0.9442 0.00896 0.00436 -0.1100 0.4678 1.0000
5.000 0.9397 0.00980 0.00487 -0.1035 0.3982 1.0000
5.250 0.9362 0.01073 0.00541 -0.0974 0.3159 1.0000
5.500 0.9332 0.01174 0.00603 -0.0915 0.2349 1.0000
5.750 0.9389 0.01250 0.00654 -0.0875 0.1813 1.0000
6.000 0.9443 0.01332 0.00707 -0.0835 0.1206 1.0000
6.250 0.9530 0.01406 0.00761 -0.0802 0.0782 1.0000
6.500 0.9672 0.01456 0.00803 -0.0779 0.0632 1.0000
6.750 0.9833 0.01497 0.00842 -0.0759 0.0532 1.0000
7.000 0.9989 0.01543 0.00883 -0.0739 0.0408 1.0000
7.250 1.0128 0.01599 0.00931 -0.0716 0.0292 1.0000
7.500 1.0287 0.01646 0.00979 -0.0697 0.0253 1.0000
7.750 1.0422 0.01709 0.01042 -0.0674 0.0210 1.0000
8.000 1.0593 0.01751 0.01088 -0.0658 0.0196 1.0000
8.250 1.0751 0.01801 0.01140 -0.0639 0.0181 1.0000
8.500 1.0895 0.01861 0.01202 -0.0619 0.0166 1.0000
8.750 1.1003 0.01945 0.01293 -0.0592 0.0152 1.0000
9.000 1.1174 0.01989 0.01341 -0.0577 0.0146 1.0000
9.250 1.1322 0.02049 0.01406 -0.0559 0.0140 1.0000
9.500 1.1476 0.02106 0.01466 -0.0542 0.0131 1.0000
9.750 1.1617 0.02172 0.01534 -0.0523 0.0124 1.0000
10.000 1.1711 0.02269 0.01637 -0.0497 0.0116 1.0000
10.250 1.1762 0.02401 0.01781 -0.0465 0.0111 1.0000
10.500 1.1921 0.02458 0.01842 -0.0450 0.0107 1.0000
10.750 1.2049 0.02538 0.01928 -0.0431 0.0103 1.0000
11.000 1.2183 0.02613 0.02009 -0.0413 0.0101 1.0000
11.250 1.2309 0.02696 0.02097 -0.0394 0.0096 1.0000
11.500 1.2452 0.02764 0.02168 -0.0380 0.0091 1.0000
11.750 1.2545 0.02875 0.02288 -0.0357 0.0091 1.0000
12.000 1.2667 0.02962 0.02378 -0.0341 0.0085 1.0000
12.250 1.2724 0.03106 0.02531 -0.0315 0.0082 1.0000
12.500 1.2736 0.03309 0.02751 -0.0283 0.0078 1.0000
12.750 1.2836 0.03426 0.02877 -0.0265 0.0077 1.0000
13.000 1.2947 0.03525 0.02984 -0.0249 0.0075 1.0000
13.250 1.3027 0.03660 0.03130 -0.0229 0.0074 1.0000
13.500 1.3091 0.03817 0.03299 -0.0208 0.0073 1.0000
13.750 1.3163 0.03957 0.03450 -0.0189 0.0071 1.0000
14.000 1.3232 0.04100 0.03603 -0.0172 0.0069 1.0000
14.250 1.3275 0.04272 0.03788 -0.0152 0.0067 1.0000
14.500 1.3300 0.04466 0.03995 -0.0132 0.0066 1.0000
14.750 1.3328 0.04654 0.04195 -0.0114 0.0065 1.0000
15.000 1.3336 0.04869 0.04423 -0.0095 0.0064 1.0000
15.250 1.3406 0.05001 0.04556 -0.0086 0.0061 1.0000
15.500 1.3390 0.05250 0.04819 -0.0069 0.0061 1.0000
15.750 1.3363 0.05512 0.05095 -0.0053 0.0060 1.0000
16.000 1.3381 0.05722 0.05309 -0.0044 0.0058 1.0000
16.250 1.3294 0.06071 0.05673 -0.0030 0.0057 1.0000
16.500 1.3168 0.06482 0.06103 -0.0018 0.0057 1.0000
16.750 1.2959 0.07014 0.06656 -0.0010 0.0055 1.0000
17.000 1.2801 0.07511 0.07172 -0.0007 0.0055 1.0000
17.250 1.2534 0.08199 0.07883 -0.0013 0.0055 1.0000
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