GOE 442 AIRFOIL (goe442-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 442 AIRFOIL (goe442-il) Reynolds number: 200,000 Max Cl/Cd: 73.04 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe442-il-200000-n5.txt Download as CSV file: xf-goe442-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 442 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3455 0.10007 0.09662 -0.0278 1.0000 0.0231
-8.250 -0.3473 0.09751 0.09411 -0.0274 1.0000 0.0232
-8.000 -0.3513 0.09510 0.09176 -0.0265 1.0000 0.0232
-6.750 -0.3618 0.07856 0.07543 -0.0248 0.9982 0.0165
-6.500 -0.3386 0.07390 0.07075 -0.0307 0.9940 0.0161
-6.250 -0.3126 0.06865 0.06547 -0.0381 0.9888 0.0159
-6.000 -0.2839 0.06294 0.05969 -0.0463 0.9835 0.0157
-5.750 -0.2516 0.05679 0.05343 -0.0549 0.9781 0.0155
-5.500 -0.2184 0.04969 0.04617 -0.0636 0.9717 0.0159
-5.000 -0.1479 0.03115 0.02670 -0.0789 0.9596 0.0171
-4.750 -0.1148 0.02687 0.02196 -0.0819 0.9547 0.0178
-4.500 -0.0826 0.02321 0.01777 -0.0838 0.9499 0.0189
-4.250 -0.0540 0.02038 0.01436 -0.0842 0.9434 0.0217
-4.000 -0.0204 0.01769 0.01106 -0.0854 0.9396 0.0239
-3.750 0.0108 0.01706 0.01031 -0.0860 0.9337 0.0259
-3.500 0.0425 0.01621 0.00918 -0.0865 0.9270 0.0302
-3.250 0.0762 0.01541 0.00827 -0.0875 0.9213 0.0336
-3.000 0.1053 0.01502 0.00774 -0.0875 0.9117 0.0383
-2.750 0.1360 0.01428 0.00687 -0.0878 0.9028 0.0426
-2.500 0.1694 0.01391 0.00645 -0.0887 0.8938 0.0476
-2.250 0.1993 0.01347 0.00588 -0.0887 0.8817 0.0517
-2.000 0.2300 0.01284 0.00520 -0.0890 0.8688 0.0559
-1.750 0.2617 0.01235 0.00468 -0.0895 0.8540 0.0593
-1.500 0.2940 0.01194 0.00418 -0.0901 0.8368 0.0629
-1.250 0.3249 0.01169 0.00382 -0.0903 0.8153 0.0670
-1.000 0.3550 0.01131 0.00337 -0.0905 0.7905 0.0723
-0.500 0.4112 0.01104 0.00279 -0.0898 0.7320 0.0838
-0.250 0.4371 0.01098 0.00260 -0.0891 0.6996 0.0957
0.000 0.4612 0.01075 0.00254 -0.0883 0.6659 0.1771
0.250 0.4843 0.01054 0.00256 -0.0873 0.6328 0.3182
0.500 0.5047 0.01008 0.00260 -0.0858 0.6037 0.5327
0.750 0.5552 0.00942 0.00259 -0.0903 0.5730 1.0000
1.000 0.5788 0.00968 0.00262 -0.0892 0.5501 1.0000
1.250 0.6027 0.00993 0.00268 -0.0883 0.5297 1.0000
1.500 0.6269 0.01018 0.00275 -0.0874 0.5119 1.0000
1.750 0.6514 0.01041 0.00284 -0.0866 0.4959 1.0000
2.000 0.6762 0.01062 0.00294 -0.0859 0.4818 1.0000
2.250 0.7012 0.01082 0.00305 -0.0852 0.4689 1.0000
2.500 0.7261 0.01102 0.00317 -0.0845 0.4562 1.0000
2.750 0.7509 0.01123 0.00331 -0.0838 0.4428 1.0000
3.000 0.7755 0.01144 0.00344 -0.0831 0.4287 1.0000
3.250 0.8000 0.01165 0.00358 -0.0824 0.4127 1.0000
3.500 0.8244 0.01187 0.00374 -0.0817 0.3973 1.0000
3.750 0.8489 0.01209 0.00391 -0.0810 0.3843 1.0000
4.250 0.8981 0.01255 0.00432 -0.0796 0.3599 1.0000
4.500 0.9224 0.01279 0.00453 -0.0789 0.3470 1.0000
4.750 0.9466 0.01304 0.00477 -0.0782 0.3336 1.0000
5.000 0.9705 0.01332 0.00502 -0.0774 0.3191 1.0000
5.250 0.9941 0.01361 0.00531 -0.0767 0.3031 1.0000
5.500 1.0171 0.01395 0.00560 -0.0758 0.2841 1.0000
5.750 1.0398 0.01433 0.00592 -0.0749 0.2597 1.0000
6.000 1.0614 0.01480 0.00630 -0.0739 0.2296 1.0000
6.250 1.0822 0.01536 0.00672 -0.0728 0.2007 1.0000
6.500 1.1030 0.01594 0.00721 -0.0716 0.1813 1.0000
6.750 1.1238 0.01650 0.00773 -0.0705 0.1687 1.0000
7.000 1.1454 0.01699 0.00827 -0.0695 0.1607 1.0000
7.250 1.1657 0.01757 0.00884 -0.0683 0.1547 1.0000
7.500 1.1873 0.01804 0.00940 -0.0673 0.1501 1.0000
7.750 1.2078 0.01858 0.00999 -0.0662 0.1457 1.0000
8.000 1.2271 0.01921 0.01065 -0.0649 0.1417 1.0000
8.250 1.2473 0.01977 0.01132 -0.0637 0.1388 1.0000
8.500 1.2679 0.02027 0.01195 -0.0625 0.1343 1.0000
8.750 1.2857 0.02095 0.01262 -0.0611 0.1274 1.0000
9.000 1.3061 0.02138 0.01318 -0.0601 0.1195 1.0000
9.250 1.3224 0.02209 0.01388 -0.0585 0.1116 1.0000
9.500 1.3433 0.02244 0.01437 -0.0576 0.1021 1.0000
9.750 1.3616 0.02297 0.01502 -0.0562 0.0932 1.0000
10.000 1.3798 0.02350 0.01561 -0.0549 0.0784 1.0000
10.250 1.3881 0.02467 0.01652 -0.0524 0.0451 1.0000
10.500 1.3887 0.02638 0.01809 -0.0488 0.0273 1.0000
10.750 1.3927 0.02785 0.01960 -0.0457 0.0208 1.0000
11.000 1.3957 0.02941 0.02123 -0.0427 0.0172 1.0000
11.250 1.4013 0.03076 0.02275 -0.0402 0.0154 1.0000
11.500 1.4050 0.03229 0.02445 -0.0377 0.0144 1.0000
11.750 1.4058 0.03409 0.02640 -0.0352 0.0135 1.0000
12.000 1.4041 0.03617 0.02865 -0.0329 0.0128 1.0000
12.250 1.3971 0.03884 0.03149 -0.0309 0.0121 1.0000
12.500 1.3927 0.04149 0.03435 -0.0294 0.0117 1.0000
12.750 1.3900 0.04419 0.03723 -0.0286 0.0112 1.0000
13.000 1.3859 0.04725 0.04047 -0.0282 0.0108 1.0000
13.250 1.3790 0.05091 0.04431 -0.0283 0.0105 1.0000
13.500 1.3713 0.05496 0.04852 -0.0290 0.0101 1.0000
13.750 1.3621 0.05952 0.05326 -0.0303 0.0099 1.0000
14.000 1.3520 0.06449 0.05838 -0.0320 0.0097 1.0000
14.250 1.3414 0.06972 0.06377 -0.0339 0.0096 1.0000
14.500 1.3296 0.07529 0.06950 -0.0362 0.0095 1.0000
14.750 1.3167 0.08118 0.07553 -0.0386 0.0093 1.0000
15.000 1.3045 0.08710 0.08160 -0.0411 0.0093 1.0000
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Polar data table (+)
Polar graphs
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