GOE 602 AIRFOIL (goe602-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 602 AIRFOIL (goe602-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.06 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe602-il-1000000.txt Download as CSV file: xf-goe602-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 602 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2976 0.11069 0.10915 -0.0341 1.0000 0.0127
-11.000 -0.2995 0.10775 0.10623 -0.0338 1.0000 0.0131
-10.250 -0.6880 0.02929 0.02688 -0.0841 0.9879 0.0083
-10.000 -0.6535 0.03013 0.02782 -0.0852 0.9870 0.0087
-9.750 -0.6376 0.02424 0.02132 -0.0890 0.9844 0.0089
-9.500 -0.6051 0.02381 0.02084 -0.0907 0.9836 0.0093
-9.250 -0.5889 0.02128 0.01798 -0.0904 0.9782 0.0095
-9.000 -0.5623 0.01951 0.01595 -0.0915 0.9758 0.0099
-8.750 -0.5333 0.01802 0.01422 -0.0927 0.9742 0.0104
-8.500 -0.5024 0.01690 0.01291 -0.0941 0.9730 0.0107
-8.250 -0.4734 0.01483 0.01050 -0.0954 0.9719 0.0114
-8.000 -0.4400 0.01417 0.00976 -0.0971 0.9710 0.0121
-7.750 -0.4151 0.01398 0.00956 -0.0966 0.9665 0.0126
-7.500 -0.3843 0.01372 0.00926 -0.0973 0.9638 0.0134
-7.250 -0.3527 0.01331 0.00877 -0.0983 0.9615 0.0142
-7.000 -0.3205 0.01296 0.00834 -0.0993 0.9594 0.0147
-6.750 -0.2913 0.01181 0.00707 -0.1001 0.9567 0.0161
-6.500 -0.2656 0.01166 0.00690 -0.0997 0.9510 0.0169
-6.250 -0.2362 0.01136 0.00656 -0.1000 0.9469 0.0180
-6.000 -0.2042 0.01113 0.00626 -0.1009 0.9434 0.0190
-5.750 -0.1806 0.01055 0.00560 -0.1001 0.9364 0.0203
-5.500 -0.1522 0.01017 0.00519 -0.1003 0.9310 0.0217
-5.250 -0.1252 0.00997 0.00497 -0.1001 0.9247 0.0230
-5.000 -0.0981 0.00971 0.00467 -0.1000 0.9184 0.0244
-4.750 -0.0696 0.00963 0.00454 -0.1000 0.9128 0.0256
-4.500 -0.0446 0.00920 0.00403 -0.0995 0.9059 0.0268
-4.250 -0.0189 0.00859 0.00335 -0.0991 0.8998 0.0288
-4.000 0.0066 0.00834 0.00308 -0.0986 0.8925 0.0303
-3.750 0.0340 0.00815 0.00283 -0.0984 0.8862 0.0321
-3.500 0.0599 0.00794 0.00259 -0.0979 0.8786 0.0333
-3.000 0.1134 0.00766 0.00221 -0.0974 0.8632 0.0349
-2.750 0.1395 0.00737 0.00182 -0.0969 0.8551 0.0372
-2.500 0.1659 0.00719 0.00161 -0.0965 0.8458 0.0402
-2.250 0.1924 0.00706 0.00145 -0.0961 0.8360 0.0435
-2.000 0.2190 0.00695 0.00130 -0.0958 0.8257 0.0507
-1.750 0.2439 0.00663 0.00119 -0.0952 0.8138 0.1175
-1.500 0.2682 0.00625 0.00108 -0.0946 0.8008 0.2161
-1.250 0.2932 0.00603 0.00104 -0.0941 0.7868 0.2975
-1.000 0.3184 0.00591 0.00100 -0.0936 0.7718 0.3491
-0.750 0.3430 0.00575 0.00098 -0.0929 0.7561 0.4151
-0.500 0.3665 0.00551 0.00098 -0.0921 0.7383 0.5199
-0.250 0.3885 0.00528 0.00101 -0.0909 0.7174 0.6459
0.000 0.4104 0.00515 0.00105 -0.0896 0.6962 0.7310
0.250 0.4318 0.00501 0.00109 -0.0880 0.6770 0.8128
0.500 0.4528 0.00491 0.00117 -0.0862 0.6578 0.9076
0.750 0.4955 0.00499 0.00124 -0.0894 0.6373 0.9697
1.000 0.5439 0.00515 0.00128 -0.0940 0.6131 0.9880
1.250 0.5845 0.00532 0.00133 -0.0969 0.5892 0.9982
1.500 0.6135 0.00546 0.00137 -0.0973 0.5701 1.0000
1.750 0.6355 0.00559 0.00142 -0.0960 0.5527 1.0000
2.000 0.6580 0.00573 0.00148 -0.0949 0.5344 1.0000
2.250 0.6804 0.00589 0.00155 -0.0938 0.5145 1.0000
2.500 0.7032 0.00604 0.00163 -0.0928 0.4976 1.0000
2.750 0.7261 0.00620 0.00172 -0.0917 0.4808 1.0000
3.000 0.7494 0.00636 0.00181 -0.0908 0.4645 1.0000
3.250 0.7730 0.00651 0.00191 -0.0899 0.4497 1.0000
3.500 0.7965 0.00669 0.00202 -0.0891 0.4326 1.0000
3.750 0.8188 0.00693 0.00215 -0.0880 0.4074 1.0000
4.000 0.8412 0.00720 0.00231 -0.0869 0.3801 1.0000
4.250 0.8637 0.00747 0.00246 -0.0859 0.3519 1.0000
4.500 0.8854 0.00781 0.00265 -0.0848 0.3178 1.0000
4.750 0.9056 0.00827 0.00289 -0.0835 0.2730 1.0000
5.000 0.9256 0.00876 0.00317 -0.0821 0.2308 1.0000
5.250 0.9446 0.00934 0.00351 -0.0806 0.1836 1.0000
5.500 0.9594 0.01024 0.00401 -0.0784 0.1111 1.0000
5.750 0.9788 0.01081 0.00442 -0.0770 0.0808 1.0000
6.000 0.9940 0.01171 0.00503 -0.0748 0.0255 1.0000
6.250 1.0157 0.01211 0.00544 -0.0737 0.0206 1.0000
6.500 1.0369 0.01254 0.00592 -0.0724 0.0175 1.0000
6.750 1.0590 0.01287 0.00627 -0.0715 0.0162 1.0000
7.000 1.0803 0.01326 0.00669 -0.0703 0.0149 1.0000
7.250 1.0996 0.01379 0.00727 -0.0688 0.0136 1.0000
7.500 1.1164 0.01448 0.00805 -0.0669 0.0127 1.0000
7.750 1.1367 0.01488 0.00848 -0.0656 0.0122 1.0000
8.000 1.1561 0.01531 0.00896 -0.0642 0.0116 1.0000
8.250 1.1752 0.01575 0.00942 -0.0628 0.0109 1.0000
8.500 1.1915 0.01627 0.00998 -0.0608 0.0102 1.0000
8.750 1.2042 0.01690 0.01066 -0.0583 0.0098 1.0000
9.000 1.2081 0.01800 0.01185 -0.0542 0.0093 1.0000
9.250 1.2148 0.01898 0.01291 -0.0508 0.0090 1.0000
9.500 1.2267 0.01969 0.01369 -0.0483 0.0088 1.0000
9.750 1.2389 0.02040 0.01446 -0.0460 0.0086 1.0000
10.000 1.2511 0.02112 0.01524 -0.0438 0.0083 1.0000
10.250 1.2603 0.02205 0.01624 -0.0413 0.0080 1.0000
10.500 1.2704 0.02295 0.01720 -0.0390 0.0077 1.0000
10.750 1.2790 0.02398 0.01830 -0.0366 0.0075 1.0000
11.000 1.2899 0.02486 0.01923 -0.0347 0.0073 1.0000
11.250 1.2975 0.02601 0.02044 -0.0326 0.0070 1.0000
11.500 1.3052 0.02718 0.02165 -0.0306 0.0067 1.0000
11.750 1.3050 0.02912 0.02367 -0.0280 0.0065 1.0000
12.000 1.2996 0.03195 0.02664 -0.0250 0.0063 1.0000
12.250 1.3062 0.03350 0.02829 -0.0234 0.0062 1.0000
12.500 1.3127 0.03502 0.02992 -0.0219 0.0061 1.0000
12.750 1.3168 0.03698 0.03199 -0.0203 0.0060 1.0000
13.000 1.3206 0.03895 0.03409 -0.0190 0.0059 1.0000
13.250 1.3237 0.04104 0.03628 -0.0178 0.0058 1.0000
13.500 1.3258 0.04328 0.03864 -0.0168 0.0057 1.0000
13.750 1.3245 0.04614 0.04166 -0.0158 0.0057 1.0000
14.000 1.3224 0.04909 0.04475 -0.0150 0.0056 1.0000
14.250 1.3190 0.05230 0.04812 -0.0145 0.0055 1.0000
14.500 1.3136 0.05584 0.05181 -0.0143 0.0055 1.0000
14.750 1.3076 0.05956 0.05568 -0.0145 0.0054 1.0000
15.000 1.2992 0.06384 0.06012 -0.0151 0.0054 1.0000
15.250 1.2879 0.06871 0.06517 -0.0161 0.0053 1.0000
15.500 1.2797 0.07326 0.06985 -0.0175 0.0053 1.0000
15.750 1.2641 0.07931 0.07609 -0.0195 0.0052 1.0000
16.000 1.2535 0.08471 0.08162 -0.0219 0.0052 1.0000
16.250 1.2380 0.09129 0.08837 -0.0249 0.0052 1.0000
16.500 1.2129 0.10010 0.09740 -0.0291 0.0052 1.0000
16.750 1.2003 0.10678 0.10421 -0.0329 0.0052 1.0000
17.000 1.1800 0.11540 0.11299 -0.0378 0.0052 1.0000
17.250 1.1516 0.12641 0.12420 -0.0442 0.0053 1.0000
17.500 1.1344 0.13528 0.13320 -0.0497 0.0053 1.0000
17.750 1.1065 0.14745 0.14554 -0.0573 0.0054 1.0000
18.000 1.0840 0.15907 0.15730 -0.0646 0.0054 1.0000
18.250 1.0530 0.17422 0.17258 -0.0737 0.0058 1.0000
18.500 1.0072 0.19768 0.19614 -0.0856 0.0067 1.0000
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