GOE 677 (= M 6) AIRFOIL (goe677-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 677 (= M 6) AIRFOIL (goe677-il) Reynolds number: 500,000 Max Cl/Cd: 73.28 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe677-il-500000-n5.txt Download as CSV file: xf-goe677-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 677 (= M 6) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -1.1777 0.04837 0.04534 -0.0465 1.0000 0.0166
-15.000 -1.2014 0.04323 0.03995 -0.0471 1.0000 0.0167
-14.750 -1.2107 0.04020 0.03676 -0.0460 1.0000 0.0170
-14.500 -1.2081 0.03850 0.03498 -0.0446 1.0000 0.0173
-14.250 -1.2020 0.03718 0.03359 -0.0431 1.0000 0.0177
-14.000 -1.1944 0.03602 0.03235 -0.0414 1.0000 0.0182
-13.750 -1.1878 0.03479 0.03101 -0.0394 1.0000 0.0186
-13.500 -1.1815 0.03354 0.02963 -0.0372 1.0000 0.0191
-13.250 -1.1741 0.03224 0.02816 -0.0350 1.0000 0.0197
-13.000 -1.1640 0.03086 0.02660 -0.0331 1.0000 0.0203
-12.750 -1.1518 0.02955 0.02509 -0.0315 1.0000 0.0208
-12.500 -1.1376 0.02842 0.02379 -0.0300 1.0000 0.0212
-12.250 -1.1199 0.02776 0.02311 -0.0288 1.0000 0.0218
-12.000 -1.0997 0.02732 0.02264 -0.0279 1.0000 0.0223
-11.750 -1.0794 0.02685 0.02212 -0.0271 1.0000 0.0228
-11.500 -1.0593 0.02628 0.02146 -0.0261 1.0000 0.0234
-11.250 -1.0396 0.02559 0.02067 -0.0251 1.0000 0.0240
-11.000 -1.0197 0.02484 0.01980 -0.0242 1.0000 0.0246
-10.750 -0.9996 0.02407 0.01888 -0.0232 1.0000 0.0253
-10.500 -0.9789 0.02333 0.01799 -0.0222 1.0000 0.0258
-10.250 -0.9573 0.02272 0.01723 -0.0214 1.0000 0.0262
-10.000 -0.9386 0.02167 0.01611 -0.0202 1.0000 0.0269
-9.750 -0.9167 0.02116 0.01556 -0.0194 1.0000 0.0275
-9.500 -0.8940 0.02076 0.01513 -0.0187 1.0000 0.0280
-9.250 -0.8713 0.02035 0.01467 -0.0179 1.0000 0.0286
-9.000 -0.8410 0.01979 0.01403 -0.0188 0.9846 0.0293
-8.750 -0.8093 0.01919 0.01332 -0.0200 0.9609 0.0301
-8.500 -0.7785 0.01856 0.01255 -0.0208 0.9324 0.0308
-8.250 -0.7537 0.01800 0.01181 -0.0203 0.9040 0.0313
-8.000 -0.7308 0.01750 0.01114 -0.0192 0.8779 0.0317
-7.750 -0.7073 0.01712 0.01057 -0.0183 0.8517 0.0320
-7.500 -0.6844 0.01650 0.00978 -0.0174 0.8249 0.0326
-7.250 -0.6612 0.01592 0.00906 -0.0166 0.7993 0.0333
-7.000 -0.6369 0.01549 0.00851 -0.0159 0.7773 0.0338
-6.750 -0.6119 0.01514 0.00804 -0.0154 0.7592 0.0344
-6.500 -0.5866 0.01482 0.00760 -0.0149 0.7431 0.0349
-6.250 -0.5609 0.01450 0.00718 -0.0145 0.7290 0.0356
-6.000 -0.5351 0.01418 0.00677 -0.0141 0.7173 0.0363
-5.750 -0.5091 0.01388 0.00637 -0.0138 0.7077 0.0370
-5.500 -0.4828 0.01360 0.00601 -0.0135 0.6990 0.0379
-5.250 -0.4564 0.01335 0.00568 -0.0132 0.6914 0.0387
-5.000 -0.4298 0.01309 0.00534 -0.0130 0.6845 0.0392
-4.750 -0.4038 0.01274 0.00494 -0.0126 0.6784 0.0402
-4.500 -0.3775 0.01243 0.00460 -0.0123 0.6729 0.0415
-4.250 -0.3506 0.01219 0.00434 -0.0121 0.6676 0.0428
-4.000 -0.3237 0.01200 0.00411 -0.0119 0.6628 0.0442
-3.750 -0.2965 0.01181 0.00388 -0.0118 0.6577 0.0458
-3.500 -0.2693 0.01163 0.00367 -0.0116 0.6520 0.0474
-3.250 -0.2422 0.01145 0.00345 -0.0114 0.6470 0.0494
-3.000 -0.2151 0.01126 0.00326 -0.0113 0.6427 0.0525
-2.750 -0.1875 0.01111 0.00312 -0.0112 0.6387 0.0558
-2.500 -0.1598 0.01099 0.00298 -0.0112 0.6345 0.0586
-2.250 -0.1326 0.01083 0.00281 -0.0110 0.6304 0.0626
-2.000 -0.1050 0.01069 0.00268 -0.0110 0.6263 0.0670
-1.750 -0.0771 0.01059 0.00256 -0.0109 0.6221 0.0708
-1.500 -0.0495 0.01045 0.00243 -0.0109 0.6180 0.0764
-1.250 -0.0220 0.01034 0.00233 -0.0108 0.6141 0.0833
-1.000 0.0056 0.01020 0.00224 -0.0108 0.6100 0.0961
-0.750 0.0329 0.01001 0.00218 -0.0107 0.6051 0.1272
-0.500 0.0601 0.00985 0.00210 -0.0106 0.6000 0.1556
-0.250 0.0867 0.00961 0.00202 -0.0104 0.5954 0.2022
0.000 0.1117 0.00915 0.00196 -0.0101 0.5904 0.3177
0.250 0.1308 0.00819 0.00181 -0.0087 0.5851 0.5513
0.500 0.1436 0.00719 0.00191 -0.0051 0.5800 0.8455
0.750 0.1710 0.00722 0.00202 -0.0046 0.5730 0.8860
1.000 0.1983 0.00731 0.00210 -0.0042 0.5643 0.9088
1.250 0.2255 0.00740 0.00217 -0.0038 0.5523 0.9255
1.500 0.2541 0.00752 0.00226 -0.0036 0.5385 0.9378
1.750 0.2823 0.00764 0.00234 -0.0035 0.5246 0.9471
2.000 0.3130 0.00778 0.00240 -0.0039 0.5072 0.9528
2.250 0.3398 0.00794 0.00246 -0.0036 0.4855 0.9596
2.500 0.3757 0.00819 0.00259 -0.0053 0.4618 0.9635
2.750 0.4088 0.00843 0.00271 -0.0065 0.4430 0.9674
3.000 0.4350 0.00862 0.00281 -0.0062 0.4276 0.9720
3.250 0.4683 0.00881 0.00292 -0.0075 0.4121 0.9730
3.500 0.5033 0.00897 0.00303 -0.0092 0.4000 0.9741
3.750 0.5368 0.00910 0.00313 -0.0106 0.3916 0.9754
4.000 0.5675 0.00923 0.00323 -0.0114 0.3814 0.9765
4.250 0.5977 0.00933 0.00333 -0.0120 0.3724 0.9776
4.500 0.6270 0.00946 0.00343 -0.0125 0.3637 0.9790
4.750 0.6558 0.00958 0.00354 -0.0129 0.3528 0.9805
5.000 0.6834 0.00973 0.00366 -0.0130 0.3400 0.9825
5.250 0.7119 0.00990 0.00380 -0.0133 0.3234 0.9840
5.500 0.7421 0.01015 0.00396 -0.0141 0.2999 0.9848
5.750 0.7709 0.01052 0.00418 -0.0148 0.2645 0.9858
6.000 0.7983 0.01102 0.00449 -0.0153 0.2243 0.9869
6.250 0.8255 0.01152 0.00484 -0.0157 0.1907 0.9882
6.500 0.8517 0.01209 0.00523 -0.0159 0.1574 0.9897
6.750 0.8771 0.01269 0.00565 -0.0161 0.1211 0.9914
7.000 0.9025 0.01326 0.00608 -0.0161 0.0981 0.9932
7.250 0.9301 0.01369 0.00647 -0.0166 0.0892 0.9944
7.500 0.9588 0.01400 0.00681 -0.0172 0.0850 0.9955
7.750 0.9868 0.01436 0.00718 -0.0177 0.0810 0.9966
8.000 1.0141 0.01476 0.00759 -0.0182 0.0772 0.9979
8.250 1.0418 0.01511 0.00798 -0.0186 0.0739 0.9991
8.500 1.0677 0.01540 0.00831 -0.0186 0.0703 1.0000
8.750 1.0849 0.01574 0.00866 -0.0169 0.0657 1.0000
9.000 1.1015 0.01610 0.00903 -0.0151 0.0613 1.0000
9.250 1.1171 0.01649 0.00939 -0.0131 0.0513 1.0000
9.500 1.1250 0.01732 0.01002 -0.0100 0.0284 1.0000
9.750 1.1331 0.01810 0.01075 -0.0069 0.0201 1.0000
10.000 1.1444 0.01869 0.01137 -0.0043 0.0175 1.0000
10.250 1.1556 0.01928 0.01199 -0.0018 0.0160 1.0000
10.500 1.1660 0.01995 0.01271 0.0008 0.0148 1.0000
10.750 1.1760 0.02059 0.01342 0.0033 0.0141 1.0000
11.000 1.1853 0.02125 0.01414 0.0059 0.0136 1.0000
11.250 1.1951 0.02203 0.01499 0.0081 0.0130 1.0000
11.500 1.2051 0.02294 0.01597 0.0099 0.0125 1.0000
11.750 1.2144 0.02401 0.01711 0.0115 0.0120 1.0000
12.000 1.2225 0.02528 0.01844 0.0129 0.0114 1.0000
12.250 1.2280 0.02687 0.02012 0.0141 0.0109 1.0000
12.500 1.2370 0.02830 0.02163 0.0149 0.0107 1.0000
12.750 1.2458 0.02981 0.02323 0.0155 0.0104 1.0000
13.000 1.2534 0.03152 0.02502 0.0160 0.0101 1.0000
13.250 1.2599 0.03340 0.02700 0.0164 0.0098 1.0000
13.500 1.2653 0.03545 0.02913 0.0166 0.0096 1.0000
13.750 1.2698 0.03763 0.03141 0.0168 0.0094 1.0000
14.000 1.2731 0.03996 0.03383 0.0168 0.0091 1.0000
14.250 1.2752 0.04246 0.03642 0.0168 0.0090 1.0000
14.500 1.2760 0.04513 0.03919 0.0167 0.0088 1.0000
14.750 1.2750 0.04805 0.04219 0.0165 0.0086 1.0000
15.000 1.2721 0.05124 0.04548 0.0162 0.0085 1.0000
15.250 1.2674 0.05471 0.04904 0.0157 0.0084 1.0000
15.500 1.2608 0.05856 0.05299 0.0149 0.0082 1.0000
15.750 1.2522 0.06287 0.05740 0.0139 0.0081 1.0000
16.000 1.2494 0.06655 0.06119 0.0129 0.0080 1.0000
16.250 1.2460 0.07040 0.06516 0.0117 0.0079 1.0000
16.500 1.2415 0.07453 0.06939 0.0104 0.0079 1.0000
16.750 1.2367 0.07877 0.07375 0.0090 0.0077 1.0000
17.000 1.2307 0.08321 0.07829 0.0074 0.0076 1.0000
17.250 1.2239 0.08786 0.08305 0.0057 0.0076 1.0000
17.500 1.2167 0.09263 0.08793 0.0039 0.0075 1.0000
17.750 1.2087 0.09758 0.09298 0.0020 0.0074 1.0000
18.000 1.2003 0.10265 0.09817 0.0000 0.0073 1.0000
18.250 1.1918 0.10783 0.10345 -0.0022 0.0072 1.0000
18.500 1.1831 0.11313 0.10886 -0.0044 0.0071 1.0000
18.750 1.1744 0.11852 0.11435 -0.0068 0.0071 1.0000
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Polar data table (+)
Polar graphs
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