GOE 393 AIRFOIL (goe393-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 393 AIRFOIL (goe393-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.4 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe393-il-1000000.txt Download as CSV file: xf-goe393-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 393 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5001 0.10075 0.09923 0.0170 1.0000 0.0158
-8.250 -0.4960 0.09676 0.09525 0.0147 1.0000 0.0158
-8.000 -0.4949 0.09232 0.09083 0.0133 1.0000 0.0162
-7.750 -0.4850 0.09001 0.08853 0.0122 1.0000 0.0164
-7.500 -0.4734 0.08733 0.08586 0.0099 1.0000 0.0168
-7.250 -0.4600 0.08431 0.08285 0.0067 1.0000 0.0173
-7.000 -0.4452 0.08082 0.07936 0.0028 1.0000 0.0182
-6.250 -0.3829 0.06035 0.05875 -0.0223 1.0000 0.0204
-6.000 -0.3562 0.05815 0.05649 -0.0254 0.9479 0.0209
-5.750 -0.3441 0.05716 0.05501 -0.0242 0.7951 0.0214
-5.500 -0.3217 0.05508 0.05267 -0.0261 0.7407 0.0223
-5.250 -0.2847 0.05025 0.04761 -0.0324 0.7155 0.0253
-4.750 -0.2270 0.01620 0.01160 -0.0492 0.6982 0.0261
-4.500 -0.2011 0.01439 0.00947 -0.0492 0.6814 0.0268
-4.250 -0.1740 0.01373 0.00866 -0.0491 0.6666 0.0275
-4.000 -0.1466 0.01326 0.00805 -0.0490 0.6528 0.0282
-3.750 -0.1192 0.01252 0.00712 -0.0489 0.6402 0.0287
-3.500 -0.0916 0.01178 0.00621 -0.0487 0.6290 0.0291
-3.250 -0.0640 0.01115 0.00541 -0.0485 0.6191 0.0294
-2.750 -0.0083 0.01015 0.00415 -0.0481 0.5999 0.0304
-2.500 0.0196 0.00985 0.00376 -0.0479 0.5908 0.0311
-2.250 0.0475 0.00956 0.00338 -0.0477 0.5819 0.0317
-2.000 0.0755 0.00931 0.00305 -0.0475 0.5741 0.0320
-1.750 0.1035 0.00911 0.00278 -0.0473 0.5661 0.0323
-1.500 0.1313 0.00867 0.00226 -0.0471 0.5589 0.0329
-1.250 0.1592 0.00837 0.00189 -0.0469 0.5512 0.0337
-1.000 0.1873 0.00817 0.00164 -0.0468 0.5438 0.0346
-0.750 0.2153 0.00802 0.00146 -0.0466 0.5359 0.0358
-0.500 0.2434 0.00790 0.00131 -0.0464 0.5288 0.0375
-0.250 0.2715 0.00781 0.00119 -0.0463 0.5213 0.0396
0.000 0.2997 0.00774 0.00109 -0.0461 0.5144 0.0428
0.250 0.3277 0.00761 0.00108 -0.0460 0.5068 0.0665
0.500 0.3559 0.00764 0.00113 -0.0459 0.4996 0.0810
0.750 0.3841 0.00771 0.00118 -0.0458 0.4917 0.0860
1.000 0.4122 0.00771 0.00118 -0.0457 0.4836 0.0911
1.500 0.4684 0.00777 0.00121 -0.0454 0.4618 0.0978
1.750 0.4965 0.00782 0.00125 -0.0453 0.4526 0.1001
2.000 0.5244 0.00781 0.00122 -0.0452 0.4426 0.1046
2.250 0.5524 0.00783 0.00124 -0.0451 0.4301 0.1082
2.500 0.5803 0.00789 0.00126 -0.0450 0.4152 0.1113
2.750 0.6082 0.00797 0.00130 -0.0449 0.4015 0.1144
3.000 0.6360 0.00800 0.00133 -0.0448 0.3883 0.1208
3.250 0.6638 0.00807 0.00139 -0.0448 0.3760 0.1258
3.500 0.6916 0.00814 0.00145 -0.0447 0.3659 0.1346
3.750 0.7193 0.00818 0.00155 -0.0446 0.3563 0.1598
4.000 0.7460 0.00660 0.00177 -0.0448 0.3481 1.0000
4.250 0.7736 0.00676 0.00187 -0.0446 0.3394 1.0000
4.500 0.8013 0.00687 0.00197 -0.0445 0.3318 1.0000
4.750 0.8288 0.00702 0.00210 -0.0444 0.3231 1.0000
5.000 0.8563 0.00717 0.00222 -0.0442 0.3135 1.0000
5.250 0.8837 0.00734 0.00236 -0.0441 0.3011 1.0000
5.500 0.9107 0.00758 0.00252 -0.0440 0.2807 1.0000
5.750 0.9373 0.00790 0.00271 -0.0438 0.2470 1.0000
6.250 0.9869 0.00938 0.00359 -0.0434 0.1316 1.0000
6.500 1.0127 0.00983 0.00394 -0.0432 0.1094 1.0000
6.750 1.0389 0.01020 0.00425 -0.0430 0.0964 1.0000
7.250 1.0914 0.01085 0.00486 -0.0427 0.0792 1.0000
7.500 1.1174 0.01120 0.00518 -0.0425 0.0688 1.0000
7.750 1.1416 0.01188 0.00567 -0.0422 0.0418 1.0000
8.000 1.1655 0.01262 0.00631 -0.0418 0.0266 1.0000
8.250 1.1903 0.01315 0.00685 -0.0414 0.0217 1.0000
8.500 1.2146 0.01376 0.00749 -0.0410 0.0184 1.0000
8.750 1.2394 0.01421 0.00797 -0.0407 0.0169 1.0000
9.000 1.2632 0.01483 0.00861 -0.0403 0.0152 1.0000
9.250 1.2862 0.01556 0.00942 -0.0397 0.0140 1.0000
9.500 1.3101 0.01608 0.01000 -0.0393 0.0134 1.0000
9.750 1.3334 0.01667 0.01064 -0.0389 0.0126 1.0000
10.000 1.3561 0.01732 0.01134 -0.0384 0.0120 1.0000
10.250 1.3764 0.01827 0.01235 -0.0377 0.0112 1.0000
10.500 1.3946 0.01946 0.01365 -0.0368 0.0105 1.0000
10.750 1.4165 0.02006 0.01432 -0.0362 0.0102 1.0000
11.000 1.4368 0.02083 0.01517 -0.0355 0.0098 1.0000
11.250 1.4561 0.02168 0.01609 -0.0347 0.0094 1.0000
11.500 1.4744 0.02257 0.01705 -0.0339 0.0091 1.0000
11.750 1.4915 0.02353 0.01808 -0.0330 0.0088 1.0000
12.000 1.5061 0.02467 0.01929 -0.0319 0.0085 1.0000
12.250 1.5143 0.02634 0.02106 -0.0304 0.0081 1.0000
12.500 1.5082 0.02881 0.02370 -0.0275 0.0079 1.0000
12.750 1.5052 0.03117 0.02619 -0.0260 0.0078 1.0000
13.000 1.5107 0.03316 0.02829 -0.0258 0.0077 1.0000
13.250 1.5151 0.03562 0.03087 -0.0263 0.0076 1.0000
13.500 1.5180 0.03847 0.03384 -0.0271 0.0075 1.0000
13.750 1.5189 0.04167 0.03716 -0.0282 0.0074 1.0000
14.000 1.5175 0.04518 0.04079 -0.0292 0.0073 1.0000
14.250 1.5151 0.04880 0.04452 -0.0303 0.0072 1.0000
14.500 1.5108 0.05269 0.04852 -0.0315 0.0071 1.0000
14.750 1.5054 0.05672 0.05267 -0.0327 0.0070 1.0000
15.000 1.4980 0.06107 0.05713 -0.0340 0.0069 1.0000
15.250 1.4893 0.06562 0.06180 -0.0354 0.0068 1.0000
15.500 1.4806 0.07027 0.06656 -0.0370 0.0067 1.0000
15.750 1.4700 0.07524 0.07163 -0.0387 0.0067 1.0000
16.000 1.4597 0.08041 0.07691 -0.0406 0.0066 1.0000
16.250 1.4494 0.08581 0.08242 -0.0428 0.0065 1.0000
16.500 1.4386 0.09141 0.08812 -0.0451 0.0065 1.0000
16.750 1.4265 0.09735 0.09418 -0.0476 0.0064 1.0000
17.000 1.4146 0.10337 0.10030 -0.0501 0.0064 1.0000
17.250 1.4017 0.10965 0.10668 -0.0529 0.0064 1.0000
17.500 1.3886 0.11612 0.11326 -0.0558 0.0063 1.0000
17.750 1.3745 0.12292 0.12018 -0.0590 0.0063 1.0000
18.000 1.3608 0.12974 0.12710 -0.0623 0.0063 1.0000
18.250 1.3465 0.13690 0.13437 -0.0659 0.0062 1.0000
18.500 1.3322 0.14428 0.14186 -0.0698 0.0062 1.0000
18.750 1.3176 0.15198 0.14967 -0.0740 0.0062 1.0000
19.000 1.3018 0.16024 0.15805 -0.0787 0.0062 1.0000
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