GOE 398 AIRFOIL (goe398-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 398 AIRFOIL (goe398-il) Reynolds number: 100,000 Max Cl/Cd: 50.05 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe398-il-100000.txt Download as CSV file: xf-goe398-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 398 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3528 0.10829 0.10384 -0.0297 1.0000 0.1281
-8.750 -0.3911 0.10839 0.10407 -0.0283 1.0000 0.1288
-8.500 -0.4260 0.10801 0.10382 -0.0265 1.0000 0.1291
-8.250 -0.3894 0.10299 0.09878 -0.0227 1.0000 0.1323
-8.000 -0.3711 0.10007 0.09585 -0.0237 0.9969 0.1365
-7.750 -0.3876 0.09689 0.09271 -0.0342 0.9854 0.1435
-7.500 -0.3804 0.09172 0.08754 -0.0390 0.9779 0.1463
-7.250 -0.3465 0.08880 0.08460 -0.0377 0.9744 0.1506
-7.000 -0.3644 0.08263 0.07828 -0.0543 0.9584 0.1612
-6.750 -0.3263 0.08033 0.07609 -0.0492 0.9574 0.1648
-6.500 -0.3155 0.07773 0.07346 -0.0502 0.9484 0.1718
-6.250 -0.3038 0.07252 0.06816 -0.0575 0.9406 0.1807
-6.000 -0.2901 0.07020 0.06584 -0.0567 0.9315 0.1857
-5.750 -0.2796 0.06555 0.06101 -0.0626 0.9219 0.1976
-5.500 -0.2716 0.05303 0.04767 -0.0715 0.9121 0.1412
-5.250 -0.2722 0.04197 0.03538 -0.0716 0.9032 0.1063
-5.000 -0.2480 0.03742 0.02964 -0.0715 0.8959 0.1019
-4.750 -0.2182 0.03514 0.02720 -0.0724 0.8892 0.1039
-4.500 -0.1937 0.03405 0.02603 -0.0720 0.8810 0.1071
-4.250 -0.1538 0.03220 0.02380 -0.0738 0.8766 0.1100
-4.000 -0.1368 0.03128 0.02256 -0.0718 0.8674 0.1124
-3.750 -0.1012 0.02992 0.02099 -0.0729 0.8617 0.1177
-3.500 -0.0545 0.02871 0.01967 -0.0758 0.8583 0.1255
-3.250 -0.0419 0.02829 0.01911 -0.0730 0.8473 0.1307
-3.000 0.0016 0.02733 0.01813 -0.0752 0.8428 0.1439
-2.750 0.0533 0.02608 0.01700 -0.0789 0.8403 0.1641
-2.500 0.0605 0.02612 0.01703 -0.0751 0.8276 0.1782
-2.250 0.1091 0.02494 0.01606 -0.0782 0.8244 0.2167
-2.000 0.1232 0.02466 0.01594 -0.0756 0.8135 0.2505
-1.750 0.1638 0.02343 0.01521 -0.0774 0.8086 0.3281
-1.500 0.2095 0.02199 0.01452 -0.0797 0.8053 0.4807
-1.250 0.4165 0.01956 0.01324 -0.1119 0.8086 1.0000
-1.000 0.4397 0.01953 0.01301 -0.1108 0.7987 1.0000
-0.750 0.4706 0.01931 0.01259 -0.1108 0.7899 1.0000
-0.500 0.4900 0.01941 0.01255 -0.1090 0.7786 1.0000
-0.250 0.5264 0.01905 0.01200 -0.1098 0.7708 1.0000
0.000 0.5431 0.01923 0.01207 -0.1075 0.7581 1.0000
0.250 0.5801 0.01887 0.01154 -0.1083 0.7502 1.0000
0.500 0.5991 0.01898 0.01155 -0.1063 0.7373 1.0000
0.750 0.6206 0.01905 0.01152 -0.1047 0.7250 1.0000
1.000 0.6577 0.01870 0.01100 -0.1055 0.7165 1.0000
1.250 0.6754 0.01887 0.01110 -0.1033 0.7026 1.0000
1.500 0.6974 0.01897 0.01111 -0.1018 0.6898 1.0000
1.750 0.7288 0.01882 0.01080 -0.1017 0.6797 1.0000
2.000 0.7517 0.01888 0.01078 -0.1004 0.6667 1.0000
2.250 0.7724 0.01905 0.01089 -0.0987 0.6536 1.0000
2.500 0.7982 0.01909 0.01082 -0.0978 0.6419 1.0000
2.750 0.8264 0.01907 0.01066 -0.0974 0.6307 1.0000
3.000 0.8450 0.01933 0.01088 -0.0954 0.6174 1.0000
3.250 0.8682 0.01950 0.01099 -0.0942 0.6058 1.0000
3.500 0.8973 0.01952 0.01086 -0.0940 0.5954 1.0000
3.750 0.9141 0.01986 0.01121 -0.0918 0.5828 1.0000
4.000 0.9369 0.02008 0.01138 -0.0906 0.5718 1.0000
4.250 0.9642 0.02017 0.01135 -0.0902 0.5614 1.0000
4.500 0.9809 0.02055 0.01175 -0.0880 0.5495 1.0000
4.750 1.0046 0.02078 0.01193 -0.0871 0.5391 1.0000
5.000 1.0289 0.02099 0.01206 -0.0862 0.5285 1.0000
5.250 1.0466 0.02139 0.01249 -0.0842 0.5173 1.0000
5.500 1.0718 0.02164 0.01266 -0.0836 0.5071 1.0000
5.750 1.0931 0.02196 0.01295 -0.0822 0.4959 1.0000
6.000 1.1115 0.02242 0.01342 -0.0805 0.4849 1.0000
6.250 1.1387 0.02275 0.01364 -0.0802 0.4749 1.0000
6.500 1.1561 0.02326 0.01420 -0.0783 0.4638 1.0000
6.750 1.1762 0.02382 0.01474 -0.0770 0.4533 1.0000
7.000 1.2046 0.02424 0.01504 -0.0770 0.4431 1.0000
7.250 1.2166 0.02494 0.01586 -0.0743 0.4321 1.0000
7.500 1.2408 0.02553 0.01638 -0.0737 0.4223 1.0000
7.750 1.2586 0.02618 0.01707 -0.0721 0.4123 1.0000
8.000 1.2777 0.02695 0.01788 -0.0707 0.4033 1.0000
8.250 1.2982 0.02762 0.01857 -0.0696 0.3944 1.0000
8.500 1.3157 0.02848 0.01950 -0.0681 0.3863 1.0000
8.750 1.3338 0.02914 0.02021 -0.0666 0.3778 1.0000
9.000 1.3508 0.02987 0.02099 -0.0649 0.3695 1.0000
9.250 1.3669 0.03039 0.02154 -0.0631 0.3608 1.0000
9.500 1.3821 0.03106 0.02226 -0.0612 0.3527 1.0000
9.750 1.3962 0.03153 0.02279 -0.0590 0.3443 1.0000
10.000 1.4128 0.03217 0.02346 -0.0574 0.3371 1.0000
10.250 1.4208 0.03285 0.02427 -0.0545 0.3297 1.0000
10.500 1.4436 0.03320 0.02455 -0.0538 0.3223 1.0000
10.750 1.4425 0.03405 0.02562 -0.0495 0.3154 1.0000
11.000 1.4736 0.03415 0.02556 -0.0500 0.3078 1.0000
11.250 1.4622 0.03527 0.02696 -0.0444 0.3023 1.0000
11.500 1.4733 0.03558 0.02728 -0.0419 0.2950 1.0000
11.750 1.4772 0.03630 0.02809 -0.0387 0.2884 1.0000
12.000 1.4764 0.03717 0.02909 -0.0351 0.2819 1.0000
12.250 1.4950 0.03748 0.02935 -0.0339 0.2749 1.0000
12.500 1.4834 0.03890 0.03101 -0.0295 0.2689 1.0000
12.750 1.5055 0.03891 0.03089 -0.0288 0.2605 1.0000
13.000 1.4870 0.04083 0.03312 -0.0243 0.2549 1.0000
13.250 1.4973 0.04126 0.03349 -0.0225 0.2462 1.0000
13.500 1.4821 0.04335 0.03582 -0.0192 0.2395 1.0000
13.750 1.4889 0.04403 0.03640 -0.0174 0.2295 1.0000
14.000 1.4675 0.04686 0.03951 -0.0145 0.2220 1.0000
14.250 1.4607 0.04874 0.04139 -0.0126 0.2117 1.0000
14.500 1.4512 0.05098 0.04364 -0.0110 0.2005 1.0000
14.750 1.4287 0.05482 0.04766 -0.0096 0.1899 1.0000
15.000 1.4110 0.05855 0.05143 -0.0087 0.1778 1.0000
15.250 1.3943 0.06251 0.05539 -0.0083 0.1655 1.0000
15.500 1.3810 0.06641 0.05924 -0.0081 0.1543 1.0000
15.750 1.3706 0.07019 0.06296 -0.0081 0.1447 1.0000
16.000 1.3569 0.07478 0.06766 -0.0086 0.1369 1.0000
16.250 1.3542 0.07785 0.07063 -0.0086 0.1298 1.0000
16.500 1.3443 0.08223 0.07515 -0.0093 0.1241 1.0000
16.750 1.3490 0.08435 0.07712 -0.0090 0.1184 1.0000
17.000 1.3383 0.08906 0.08204 -0.0100 0.1145 1.0000
17.250 1.3391 0.09199 0.08497 -0.0103 0.1103 1.0000
17.500 1.3459 0.09398 0.08693 -0.0100 0.1063 1.0000
17.750 1.3351 0.09891 0.09207 -0.0113 0.1037 1.0000
18.000 1.3312 0.10275 0.09602 -0.0122 0.1008 1.0000
18.250 1.3599 0.10129 0.09430 -0.0102 0.0964 1.0000
18.500 1.3399 0.10777 0.10108 -0.0126 0.0950 1.0000
18.750 1.3200 0.11450 0.10806 -0.0154 0.0937 1.0000
19.000 1.2944 0.12245 0.11627 -0.0190 0.0928 1.0000
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