GOE 766 AIRFOIL (goe766-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 766 AIRFOIL (goe766-il) Reynolds number: 200,000 Max Cl/Cd: 57.23 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe766-il-200000-n5.txt Download as CSV file: xf-goe766-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 766 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.9381 0.05758 0.05251 -0.0433 1.0000 0.0326
-13.250 -0.9559 0.05304 0.04780 -0.0450 1.0000 0.0327
-13.000 -0.9641 0.05008 0.04472 -0.0453 1.0000 0.0329
-12.750 -0.9730 0.04734 0.04185 -0.0447 1.0000 0.0331
-12.500 -0.9782 0.04520 0.03959 -0.0433 1.0000 0.0334
-12.250 -0.9824 0.04330 0.03756 -0.0413 1.0000 0.0337
-12.000 -0.9850 0.04168 0.03582 -0.0387 1.0000 0.0341
-11.750 -0.9875 0.04004 0.03402 -0.0357 1.0000 0.0345
-11.500 -0.9852 0.03834 0.03214 -0.0332 1.0000 0.0351
-11.250 -0.9812 0.03654 0.03010 -0.0308 1.0000 0.0357
-11.000 -0.9753 0.03471 0.02799 -0.0285 1.0000 0.0363
-10.750 -0.9668 0.03296 0.02594 -0.0263 1.0000 0.0369
-10.500 -0.9558 0.03144 0.02415 -0.0242 1.0000 0.0375
-10.250 -0.9390 0.03034 0.02305 -0.0229 1.0000 0.0381
-10.000 -0.9218 0.02940 0.02206 -0.0215 1.0000 0.0387
-9.750 -0.9046 0.02844 0.02101 -0.0200 1.0000 0.0394
-9.500 -0.8870 0.02745 0.01991 -0.0185 1.0000 0.0401
-9.250 -0.8690 0.02641 0.01875 -0.0171 1.0000 0.0408
-9.000 -0.8504 0.02542 0.01760 -0.0156 1.0000 0.0415
-8.750 -0.8314 0.02451 0.01655 -0.0141 1.0000 0.0424
-8.500 -0.8118 0.02372 0.01559 -0.0126 1.0000 0.0432
-8.250 -0.7923 0.02276 0.01465 -0.0113 1.0000 0.0440
-8.000 -0.7724 0.02201 0.01390 -0.0099 1.0000 0.0448
-7.750 -0.7525 0.02130 0.01318 -0.0085 1.0000 0.0457
-7.500 -0.7324 0.02063 0.01247 -0.0071 1.0000 0.0466
-7.250 -0.7122 0.01997 0.01177 -0.0056 1.0000 0.0475
-7.000 -0.6920 0.01938 0.01112 -0.0041 1.0000 0.0487
-6.750 -0.6716 0.01884 0.01050 -0.0026 1.0000 0.0499
-6.500 -0.6526 0.01816 0.00986 -0.0010 1.0000 0.0512
-6.250 -0.6334 0.01761 0.00933 0.0006 1.0000 0.0524
-6.000 -0.6140 0.01712 0.00884 0.0023 1.0000 0.0537
-5.750 -0.5946 0.01665 0.00837 0.0040 1.0000 0.0553
-5.500 -0.5704 0.01620 0.00789 0.0047 0.9983 0.0571
-5.250 -0.5351 0.01562 0.00733 0.0030 0.9899 0.0598
-5.000 -0.4994 0.01513 0.00687 0.0013 0.9805 0.0634
-4.750 -0.4637 0.01470 0.00641 -0.0002 0.9693 0.0674
-4.500 -0.4282 0.01418 0.00596 -0.0018 0.9563 0.0729
-4.250 -0.3924 0.01374 0.00556 -0.0033 0.9401 0.0805
-4.000 -0.3553 0.01329 0.00520 -0.0051 0.9190 0.0947
-3.750 -0.3158 0.01288 0.00488 -0.0073 0.8914 0.1185
-3.500 -0.2798 0.01258 0.00458 -0.0087 0.8496 0.1428
-3.250 -0.2488 0.01236 0.00426 -0.0089 0.7878 0.1631
-3.000 -0.2244 0.01225 0.00399 -0.0077 0.7259 0.1838
-2.750 -0.2019 0.01215 0.00377 -0.0064 0.6772 0.2091
-2.500 -0.1800 0.01194 0.00357 -0.0050 0.6394 0.2495
-2.000 -0.1388 0.01125 0.00327 -0.0021 0.5831 0.4053
-1.750 -0.1205 0.01080 0.00320 0.0000 0.5615 0.5086
-1.500 -0.1011 0.01050 0.00321 0.0020 0.5426 0.6107
-1.250 -0.0785 0.01037 0.00322 0.0036 0.5256 0.6718
-1.000 -0.0538 0.01033 0.00321 0.0047 0.5107 0.7115
-0.750 -0.0281 0.01032 0.00321 0.0055 0.4965 0.7416
-0.500 -0.0017 0.01035 0.00323 0.0063 0.4829 0.7712
-0.250 0.0261 0.01037 0.00329 0.0068 0.4695 0.8048
0.000 0.0560 0.01044 0.00337 0.0070 0.4572 0.8390
0.250 0.0894 0.01057 0.00346 0.0063 0.4456 0.8652
0.500 0.1235 0.01070 0.00355 0.0055 0.4338 0.8851
0.750 0.1589 0.01085 0.00364 0.0043 0.4220 0.9013
1.000 0.1947 0.01102 0.00372 0.0030 0.4101 0.9151
1.250 0.2306 0.01118 0.00382 0.0017 0.3980 0.9289
1.500 0.2666 0.01136 0.00395 0.0004 0.3870 0.9425
1.750 0.3069 0.01155 0.00405 -0.0020 0.3756 0.9498
2.000 0.3415 0.01171 0.00416 -0.0032 0.3643 0.9589
2.250 0.3789 0.01186 0.00425 -0.0050 0.3528 0.9654
2.500 0.4123 0.01202 0.00433 -0.0061 0.3422 0.9722
2.750 0.4481 0.01215 0.00442 -0.0077 0.3315 0.9773
3.000 0.4811 0.01230 0.00452 -0.0087 0.3224 0.9832
3.250 0.5171 0.01244 0.00461 -0.0105 0.3125 0.9877
3.500 0.5516 0.01259 0.00473 -0.0119 0.3036 0.9926
3.750 0.5869 0.01275 0.00483 -0.0135 0.2951 0.9970
4.000 0.6190 0.01289 0.00496 -0.0145 0.2857 1.0000
4.250 0.6400 0.01308 0.00508 -0.0132 0.2783 1.0000
4.500 0.6618 0.01324 0.00526 -0.0120 0.2714 1.0000
4.750 0.6833 0.01344 0.00542 -0.0108 0.2647 1.0000
5.000 0.7049 0.01364 0.00561 -0.0096 0.2577 1.0000
5.250 0.7266 0.01384 0.00581 -0.0084 0.2493 1.0000
5.500 0.7482 0.01407 0.00602 -0.0072 0.2416 1.0000
5.750 0.7701 0.01429 0.00624 -0.0060 0.2340 1.0000
6.000 0.7916 0.01455 0.00649 -0.0048 0.2274 1.0000
6.250 0.8138 0.01476 0.00675 -0.0037 0.2199 1.0000
6.500 0.8351 0.01505 0.00700 -0.0025 0.2129 1.0000
6.750 0.8575 0.01528 0.00730 -0.0014 0.2048 1.0000
7.000 0.8787 0.01558 0.00758 -0.0002 0.1968 1.0000
7.250 0.9008 0.01584 0.00789 0.0009 0.1872 1.0000
7.500 0.9222 0.01614 0.00821 0.0020 0.1770 1.0000
7.750 0.9432 0.01648 0.00855 0.0032 0.1653 1.0000
8.000 0.9636 0.01688 0.00892 0.0044 0.1522 1.0000
8.250 0.9833 0.01734 0.00934 0.0057 0.1385 1.0000
8.500 1.0020 0.01788 0.00985 0.0071 0.1262 1.0000
8.750 1.0199 0.01849 0.01042 0.0086 0.1154 1.0000
9.000 1.0377 0.01910 0.01102 0.0102 0.1063 1.0000
9.250 1.0550 0.01973 0.01166 0.0117 0.0989 1.0000
9.500 1.0709 0.02045 0.01238 0.0134 0.0928 1.0000
9.750 1.0877 0.02108 0.01306 0.0150 0.0879 1.0000
10.000 1.1030 0.02180 0.01381 0.0167 0.0836 1.0000
10.250 1.1166 0.02259 0.01462 0.0186 0.0801 1.0000
10.500 1.1314 0.02329 0.01541 0.0204 0.0768 1.0000
10.750 1.1440 0.02408 0.01624 0.0223 0.0739 1.0000
11.000 1.1535 0.02500 0.01718 0.0245 0.0715 1.0000
11.250 1.1615 0.02591 0.01815 0.0270 0.0696 1.0000
11.500 1.1683 0.02677 0.01911 0.0296 0.0679 1.0000
11.750 1.1738 0.02775 0.02017 0.0321 0.0664 1.0000
12.000 1.1783 0.02889 0.02139 0.0343 0.0648 1.0000
12.250 1.1813 0.03024 0.02280 0.0362 0.0635 1.0000
12.500 1.1820 0.03191 0.02451 0.0377 0.0622 1.0000
12.750 1.1816 0.03388 0.02652 0.0387 0.0611 1.0000
13.000 1.1852 0.03576 0.02854 0.0391 0.0601 1.0000
13.250 1.1876 0.03791 0.03081 0.0392 0.0590 1.0000
13.500 1.1891 0.04032 0.03333 0.0389 0.0580 1.0000
13.750 1.1900 0.04291 0.03602 0.0384 0.0572 1.0000
14.000 1.1900 0.04571 0.03892 0.0377 0.0562 1.0000
14.250 1.1892 0.04869 0.04198 0.0368 0.0553 1.0000
14.500 1.1881 0.05172 0.04508 0.0358 0.0546 1.0000
14.750 1.1861 0.05486 0.04827 0.0348 0.0538 1.0000
15.000 1.1847 0.05785 0.05127 0.0341 0.0530 1.0000
15.250 1.1822 0.06124 0.05481 0.0328 0.0523 1.0000
15.500 1.1789 0.06475 0.05846 0.0315 0.0517 1.0000
15.750 1.1747 0.06841 0.06224 0.0301 0.0509 1.0000
16.000 1.1700 0.07223 0.06618 0.0285 0.0502 1.0000
16.250 1.1652 0.07615 0.07020 0.0268 0.0495 1.0000
16.500 1.1600 0.08024 0.07439 0.0249 0.0487 1.0000
16.750 1.1550 0.08440 0.07864 0.0230 0.0480 1.0000
17.000 1.1509 0.08844 0.08275 0.0211 0.0473 1.0000
17.250 1.1478 0.09236 0.08672 0.0193 0.0466 1.0000
17.500 1.1487 0.09550 0.08988 0.0181 0.0460 1.0000
17.750 1.1375 0.10111 0.09564 0.0151 0.0454 1.0000
18.000 1.1224 0.10758 0.10230 0.0115 0.0449 1.0000
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