GOE 676 (= M 12) AIRFOIL (goe676-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 676 (= M 12) AIRFOIL (goe676-il) Reynolds number: 200,000 Max Cl/Cd: 65.46 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe676-il-200000.txt Download as CSV file: xf-goe676-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 676 (= M 12) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5197 0.11240 0.10870 -0.0142 1.0000 0.0683
-10.500 -0.5460 0.10456 0.10094 -0.0256 1.0000 0.0696
-10.250 -0.5658 0.09618 0.09258 -0.0355 1.0000 0.0698
-10.000 -0.5342 0.09626 0.09266 -0.0235 1.0000 0.0717
-9.750 -0.5243 0.09378 0.09019 -0.0227 1.0000 0.0730
-9.500 -0.5206 0.09033 0.08674 -0.0238 1.0000 0.0746
-9.250 -0.5227 0.08584 0.08228 -0.0266 1.0000 0.0766
-9.000 -0.5353 0.07937 0.07586 -0.0329 1.0000 0.0784
-8.750 -0.5627 0.07267 0.06912 -0.0383 1.0000 0.0800
-8.500 -0.5424 0.05514 0.05161 -0.0438 1.0000 0.0844
-8.250 -0.5163 0.05388 0.05048 -0.0424 1.0000 0.0866
-8.000 -0.5216 0.05108 0.04767 -0.0403 1.0000 0.0884
-7.750 -0.5360 0.04814 0.04469 -0.0371 1.0000 0.0900
-7.500 -0.5551 0.04561 0.04209 -0.0328 1.0000 0.0918
-7.250 -0.6043 0.04582 0.04170 -0.0243 1.0000 0.0964
-7.000 -0.6413 0.04003 0.03484 -0.0223 1.0000 0.0666
-6.750 -0.6421 0.03633 0.03081 -0.0186 1.0000 0.0644
-6.500 -0.6338 0.03333 0.02743 -0.0161 0.9994 0.0642
-6.250 -0.6024 0.02961 0.02316 -0.0177 0.9953 0.0640
-6.000 -0.5686 0.02703 0.02015 -0.0194 0.9910 0.0647
-5.750 -0.5327 0.02530 0.01809 -0.0214 0.9864 0.0668
-5.500 -0.4937 0.02367 0.01611 -0.0237 0.9830 0.0682
-5.250 -0.4583 0.02253 0.01469 -0.0253 0.9770 0.0694
-5.000 -0.4206 0.02051 0.01255 -0.0276 0.9731 0.0722
-4.750 -0.3789 0.01947 0.01149 -0.0307 0.9702 0.0755
-4.500 -0.3437 0.01859 0.01054 -0.0322 0.9633 0.0784
-4.250 -0.3019 0.01779 0.00964 -0.0349 0.9591 0.0819
-4.000 -0.2607 0.01661 0.00852 -0.0378 0.9559 0.0877
-3.750 -0.2287 0.01600 0.00793 -0.0386 0.9468 0.0936
-3.500 -0.1916 0.01516 0.00714 -0.0405 0.9414 0.1012
-3.250 -0.1625 0.01473 0.00671 -0.0406 0.9307 0.1111
-3.000 -0.1321 0.01422 0.00626 -0.0409 0.9218 0.1253
-2.750 -0.1057 0.01363 0.00580 -0.0403 0.9111 0.1458
-2.500 -0.0830 0.01296 0.00535 -0.0392 0.8987 0.1895
-2.250 -0.0691 0.01142 0.00494 -0.0368 0.8864 0.4315
-2.000 -0.0582 0.01016 0.00492 -0.0324 0.8753 0.7202
-1.750 -0.0331 0.01017 0.00523 -0.0299 0.8640 0.8472
-1.500 -0.0072 0.01037 0.00538 -0.0281 0.8517 0.8930
-1.250 0.0234 0.01060 0.00551 -0.0274 0.8405 0.9205
-1.000 0.0630 0.01087 0.00565 -0.0286 0.8305 0.9415
-0.750 0.1249 0.01120 0.00586 -0.0346 0.8194 0.9602
-0.500 0.1811 0.01135 0.00587 -0.0398 0.8085 0.9758
-0.250 0.2386 0.01135 0.00572 -0.0456 0.7977 0.9902
0.000 0.2917 0.01122 0.00551 -0.0510 0.7843 1.0000
0.250 0.3157 0.01115 0.00535 -0.0504 0.7708 1.0000
0.500 0.3399 0.01109 0.00521 -0.0499 0.7578 1.0000
0.750 0.3641 0.01104 0.00508 -0.0493 0.7451 1.0000
1.000 0.3884 0.01100 0.00494 -0.0487 0.7327 1.0000
1.250 0.4130 0.01096 0.00485 -0.0482 0.7196 1.0000
1.500 0.4376 0.01095 0.00478 -0.0477 0.7059 1.0000
1.750 0.4621 0.01094 0.00470 -0.0471 0.6911 1.0000
2.000 0.4865 0.01095 0.00463 -0.0464 0.6756 1.0000
2.250 0.5110 0.01098 0.00458 -0.0458 0.6598 1.0000
2.500 0.5354 0.01104 0.00456 -0.0451 0.6442 1.0000
2.750 0.5600 0.01112 0.00460 -0.0445 0.6293 1.0000
3.000 0.5843 0.01122 0.00465 -0.0439 0.6147 1.0000
3.250 0.6083 0.01133 0.00471 -0.0432 0.5996 1.0000
3.500 0.6320 0.01145 0.00479 -0.0424 0.5835 1.0000
3.750 0.6555 0.01156 0.00487 -0.0417 0.5673 1.0000
4.000 0.6788 0.01169 0.00496 -0.0408 0.5511 1.0000
4.250 0.7020 0.01182 0.00507 -0.0399 0.5350 1.0000
4.500 0.7247 0.01196 0.00518 -0.0390 0.5181 1.0000
4.750 0.7473 0.01212 0.00531 -0.0380 0.5015 1.0000
5.000 0.7698 0.01230 0.00547 -0.0370 0.4864 1.0000
5.250 0.7920 0.01250 0.00565 -0.0360 0.4706 1.0000
5.500 0.8139 0.01272 0.00584 -0.0349 0.4552 1.0000
5.750 0.8358 0.01296 0.00607 -0.0338 0.4411 1.0000
6.000 0.8574 0.01321 0.00633 -0.0327 0.4269 1.0000
6.250 0.8785 0.01348 0.00658 -0.0315 0.4109 1.0000
6.500 0.8990 0.01375 0.00683 -0.0302 0.3930 1.0000
6.750 0.9190 0.01405 0.00709 -0.0288 0.3742 1.0000
7.000 0.9387 0.01434 0.00740 -0.0274 0.3527 1.0000
7.250 0.9572 0.01470 0.00769 -0.0258 0.3278 1.0000
7.500 0.9756 0.01508 0.00804 -0.0242 0.2989 1.0000
7.750 0.9928 0.01559 0.00845 -0.0225 0.2632 1.0000
8.000 1.0080 0.01628 0.00896 -0.0207 0.2183 1.0000
8.250 1.0220 0.01714 0.00960 -0.0187 0.1812 1.0000
8.500 1.0366 0.01801 0.01032 -0.0169 0.1578 1.0000
8.750 1.0508 0.01890 0.01112 -0.0150 0.1399 1.0000
9.000 1.0631 0.01991 0.01206 -0.0130 0.1228 1.0000
9.250 1.0756 0.02091 0.01305 -0.0110 0.1013 1.0000
9.500 1.0861 0.02202 0.01405 -0.0087 0.0797 1.0000
9.750 1.0970 0.02304 0.01500 -0.0065 0.0668 1.0000
10.000 1.1024 0.02422 0.01612 -0.0035 0.0599 1.0000
10.250 1.1100 0.02537 0.01734 -0.0010 0.0552 1.0000
10.500 1.1152 0.02675 0.01873 0.0014 0.0515 1.0000
10.750 1.1200 0.02832 0.02035 0.0037 0.0486 1.0000
11.000 1.1284 0.02970 0.02182 0.0055 0.0459 1.0000
11.250 1.1352 0.03128 0.02343 0.0071 0.0439 1.0000
11.500 1.1403 0.03329 0.02540 0.0090 0.0420 1.0000
11.750 1.1505 0.03490 0.02712 0.0103 0.0405 1.0000
12.000 1.1606 0.03646 0.02882 0.0116 0.0389 1.0000
12.250 1.1702 0.03809 0.03053 0.0127 0.0373 1.0000
12.500 1.1808 0.03979 0.03223 0.0137 0.0359 1.0000
12.750 1.2007 0.04211 0.03450 0.0149 0.0344 1.0000
13.000 1.2074 0.04402 0.03664 0.0160 0.0339 1.0000
13.250 1.2132 0.04618 0.03901 0.0171 0.0332 1.0000
13.500 1.2171 0.04853 0.04159 0.0181 0.0325 1.0000
13.750 1.2194 0.05103 0.04429 0.0189 0.0317 1.0000
14.000 1.2210 0.05359 0.04701 0.0195 0.0310 1.0000
14.250 1.2223 0.05621 0.04976 0.0199 0.0303 1.0000
14.500 1.2218 0.05911 0.05279 0.0202 0.0297 1.0000
14.750 1.2209 0.06226 0.05608 0.0204 0.0293 1.0000
15.000 1.2172 0.06587 0.05984 0.0204 0.0290 1.0000
15.250 1.2097 0.07004 0.06419 0.0201 0.0288 1.0000
15.500 1.1975 0.07472 0.06908 0.0193 0.0287 1.0000
15.750 1.1818 0.07983 0.07442 0.0179 0.0286 1.0000
16.000 1.1635 0.08539 0.08020 0.0158 0.0286 1.0000
16.250 1.1423 0.09164 0.08669 0.0127 0.0287 1.0000
16.500 1.1160 0.09931 0.09463 0.0083 0.0290 1.0000
16.750 1.0261 0.12137 0.11736 -0.0071 0.0308 1.0000
17.000 0.9326 0.15026 0.14654 -0.0253 0.0336 1.0000
17.250 0.9105 0.16176 0.15804 -0.0309 0.0344 1.0000
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