GOE 682 AIRFOIL (goe682-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 682 AIRFOIL (goe682-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.52 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe682-il-1000000.txt Download as CSV file: xf-goe682-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 682 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.2724 0.12008 0.11844 -0.0386 1.0000 0.0208
-12.250 -0.2735 0.11627 0.11464 -0.0393 1.0000 0.0209
-12.000 -0.8303 0.03271 0.03039 -0.0866 0.9971 0.0196
-11.750 -0.8052 0.02997 0.02742 -0.0903 0.9947 0.0201
-11.500 -0.7799 0.02800 0.02524 -0.0926 0.9922 0.0205
-11.250 -0.7496 0.02750 0.02465 -0.0939 0.9900 0.0209
-11.000 -0.7312 0.02365 0.02045 -0.0967 0.9863 0.0216
-10.750 -0.6989 0.02315 0.01993 -0.0983 0.9849 0.0220
-10.500 -0.6658 0.02268 0.01943 -0.1000 0.9837 0.0224
-10.250 -0.6353 0.02229 0.01900 -0.1010 0.9813 0.0229
-10.000 -0.6073 0.02164 0.01827 -0.1017 0.9778 0.0235
-9.750 -0.5773 0.02070 0.01720 -0.1029 0.9753 0.0241
-9.500 -0.5451 0.01990 0.01626 -0.1045 0.9734 0.0247
-9.250 -0.5121 0.01922 0.01544 -0.1060 0.9716 0.0251
-9.000 -0.4890 0.01705 0.01298 -0.1066 0.9664 0.0258
-8.750 -0.4611 0.01636 0.01225 -0.1070 0.9612 0.0264
-8.500 -0.4291 0.01598 0.01184 -0.1081 0.9576 0.0270
-8.250 -0.4022 0.01546 0.01124 -0.1081 0.9510 0.0275
-8.000 -0.3743 0.01492 0.01060 -0.1083 0.9442 0.0280
-7.750 -0.3476 0.01439 0.00997 -0.1081 0.9366 0.0286
-7.500 -0.3207 0.01400 0.00949 -0.1080 0.9285 0.0293
-7.250 -0.2947 0.01355 0.00893 -0.1076 0.9200 0.0298
-7.000 -0.2681 0.01316 0.00843 -0.1073 0.9112 0.0301
-6.750 -0.2426 0.01276 0.00793 -0.1068 0.9009 0.0304
-6.500 -0.2205 0.01147 0.00647 -0.1059 0.8898 0.0313
-6.250 -0.1948 0.01111 0.00605 -0.1054 0.8785 0.0321
-6.000 -0.1692 0.01081 0.00567 -0.1048 0.8661 0.0326
-5.750 -0.1435 0.01051 0.00530 -0.1043 0.8537 0.0332
-5.500 -0.1177 0.01024 0.00495 -0.1037 0.8416 0.0339
-5.250 -0.0918 0.00998 0.00460 -0.1032 0.8303 0.0346
-5.000 -0.0657 0.00973 0.00428 -0.1027 0.8192 0.0352
-4.750 -0.0393 0.00953 0.00401 -0.1023 0.8086 0.0358
-4.500 -0.0126 0.00943 0.00383 -0.1018 0.7978 0.0363
-4.250 0.0121 0.00890 0.00322 -0.1011 0.7866 0.0376
-4.000 0.0383 0.00866 0.00294 -0.1007 0.7762 0.0387
-3.750 0.0648 0.00851 0.00274 -0.1003 0.7659 0.0398
-3.500 0.0914 0.00839 0.00256 -0.0999 0.7551 0.0410
-3.250 0.1182 0.00827 0.00240 -0.0995 0.7446 0.0424
-3.000 0.1450 0.00820 0.00227 -0.0991 0.7343 0.0434
-2.750 0.1713 0.00798 0.00200 -0.0986 0.7242 0.0463
-2.500 0.1983 0.00789 0.00189 -0.0983 0.7149 0.0492
-2.250 0.2250 0.00784 0.00179 -0.0979 0.7050 0.0516
-2.000 0.2516 0.00771 0.00164 -0.0975 0.6939 0.0569
-1.750 0.2785 0.00765 0.00156 -0.0972 0.6833 0.0618
-1.500 0.3049 0.00757 0.00145 -0.0967 0.6729 0.0702
-1.250 0.3318 0.00749 0.00137 -0.0964 0.6633 0.0809
-1.000 0.3581 0.00732 0.00131 -0.0960 0.6544 0.1161
-0.750 0.3840 0.00718 0.00130 -0.0956 0.6444 0.1720
-0.500 0.4110 0.00714 0.00129 -0.0953 0.6345 0.1962
-0.250 0.4376 0.00712 0.00129 -0.0950 0.6253 0.2164
0.000 0.4645 0.00709 0.00129 -0.0947 0.6149 0.2386
0.250 0.4911 0.00705 0.00130 -0.0944 0.6045 0.2659
0.500 0.5171 0.00699 0.00132 -0.0939 0.5940 0.3114
0.750 0.5427 0.00679 0.00135 -0.0935 0.5837 0.4015
1.000 0.5647 0.00629 0.00142 -0.0925 0.5741 0.6253
1.250 0.5803 0.00566 0.00154 -0.0895 0.5641 0.8971
1.500 0.6603 0.00571 0.00160 -0.1010 0.5475 0.9991
1.750 0.6873 0.00583 0.00164 -0.1007 0.5327 1.0000
2.000 0.7114 0.00595 0.00168 -0.0999 0.5172 1.0000
2.250 0.7355 0.00609 0.00174 -0.0990 0.5009 1.0000
2.500 0.7596 0.00624 0.00181 -0.0981 0.4853 1.0000
2.750 0.7836 0.00640 0.00189 -0.0973 0.4703 1.0000
3.250 0.8320 0.00671 0.00208 -0.0956 0.4436 1.0000
3.500 0.8564 0.00687 0.00218 -0.0949 0.4315 1.0000
3.750 0.8806 0.00703 0.00229 -0.0941 0.4194 1.0000
4.000 0.9047 0.00721 0.00241 -0.0933 0.4071 1.0000
4.250 0.9292 0.00738 0.00253 -0.0925 0.3951 1.0000
4.500 0.9538 0.00754 0.00265 -0.0919 0.3831 1.0000
4.750 0.9780 0.00773 0.00279 -0.0911 0.3691 1.0000
5.000 1.0016 0.00796 0.00295 -0.0903 0.3512 1.0000
5.250 1.0244 0.00824 0.00312 -0.0893 0.3285 1.0000
5.500 1.0465 0.00857 0.00333 -0.0882 0.3027 1.0000
5.750 1.0686 0.00890 0.00356 -0.0872 0.2799 1.0000
6.500 1.1349 0.00988 0.00429 -0.0841 0.2324 1.0000
6.750 1.1576 0.01015 0.00453 -0.0831 0.2233 1.0000
7.000 1.1805 0.01041 0.00476 -0.0823 0.2158 1.0000
7.250 1.2034 0.01066 0.00500 -0.0814 0.2088 1.0000
7.500 1.2260 0.01092 0.00524 -0.0805 0.2010 1.0000
7.750 1.2485 0.01117 0.00549 -0.0795 0.1944 1.0000
8.000 1.2708 0.01143 0.00573 -0.0786 0.1865 1.0000
8.250 1.2926 0.01171 0.00599 -0.0776 0.1776 1.0000
8.500 1.3131 0.01205 0.00628 -0.0764 0.1674 1.0000
8.750 1.3336 0.01237 0.00657 -0.0751 0.1556 1.0000
9.000 1.3516 0.01282 0.00693 -0.0735 0.1388 1.0000
9.250 1.3622 0.01360 0.00750 -0.0707 0.1061 1.0000
9.750 1.3732 0.01539 0.00898 -0.0633 0.0579 1.0000
10.000 1.3740 0.01659 0.00997 -0.0591 0.0304 1.0000
10.250 1.3819 0.01747 0.01081 -0.0561 0.0218 1.0000
10.500 1.3941 0.01814 0.01149 -0.0538 0.0194 1.0000
10.750 1.4051 0.01890 0.01228 -0.0515 0.0176 1.0000
11.000 1.4181 0.01956 0.01300 -0.0495 0.0166 1.0000
11.250 1.4294 0.02033 0.01381 -0.0475 0.0157 1.0000
11.500 1.4389 0.02126 0.01477 -0.0453 0.0149 1.0000
11.750 1.4466 0.02233 0.01592 -0.0430 0.0141 1.0000
12.000 1.4576 0.02322 0.01687 -0.0413 0.0137 1.0000
12.250 1.4671 0.02425 0.01797 -0.0395 0.0134 1.0000
12.500 1.4763 0.02535 0.01912 -0.0378 0.0130 1.0000
12.750 1.4839 0.02660 0.02043 -0.0362 0.0125 1.0000
13.000 1.4902 0.02801 0.02191 -0.0346 0.0121 1.0000
13.250 1.4927 0.02979 0.02376 -0.0329 0.0117 1.0000
13.500 1.4891 0.03219 0.02626 -0.0311 0.0113 1.0000
13.750 1.4958 0.03380 0.02795 -0.0301 0.0112 1.0000
14.000 1.4997 0.03572 0.02995 -0.0291 0.0110 1.0000
14.250 1.5056 0.03752 0.03182 -0.0283 0.0107 1.0000
14.500 1.5064 0.03989 0.03428 -0.0275 0.0105 1.0000
14.750 1.5078 0.04228 0.03676 -0.0269 0.0104 1.0000
15.000 1.5076 0.04494 0.03951 -0.0265 0.0101 1.0000
15.250 1.5073 0.04771 0.04235 -0.0263 0.0100 1.0000
15.500 1.5057 0.05072 0.04544 -0.0262 0.0097 1.0000
15.750 1.5020 0.05405 0.04887 -0.0263 0.0096 1.0000
16.000 1.4966 0.05775 0.05266 -0.0266 0.0095 1.0000
16.250 1.4904 0.06166 0.05666 -0.0272 0.0093 1.0000
16.500 1.4805 0.06618 0.06128 -0.0280 0.0092 1.0000
16.750 1.4704 0.07090 0.06612 -0.0291 0.0092 1.0000
17.000 1.4560 0.07641 0.07173 -0.0306 0.0090 1.0000
17.250 1.4419 0.08199 0.07743 -0.0322 0.0089 1.0000
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