GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Reynolds number: 500,000 Max Cl/Cd: 98.41 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe188-il-500000.txt Download as CSV file: xf-goe188-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2919 0.08642 0.08440 -0.0203 1.0000 0.0092
-8.250 -0.2903 0.08282 0.08082 -0.0212 1.0000 0.0093
-8.000 -0.2890 0.07923 0.07725 -0.0222 1.0000 0.0094
-7.750 -0.2882 0.07562 0.07366 -0.0232 1.0000 0.0095
-7.500 -0.2880 0.07205 0.07012 -0.0243 1.0000 0.0096
-7.250 -0.2892 0.06854 0.06664 -0.0253 1.0000 0.0097
-7.000 -0.2931 0.06524 0.06339 -0.0260 1.0000 0.0097
-6.750 -0.3007 0.06216 0.06037 -0.0266 1.0000 0.0098
-6.500 -0.2843 0.05640 0.05458 -0.0342 0.9871 0.0100
-6.250 -0.2641 0.05050 0.04863 -0.0416 0.9618 0.0102
-6.000 -0.2413 0.04471 0.04271 -0.0481 0.9263 0.0105
-5.750 -0.2913 0.05814 0.05598 -0.0448 0.9827 0.0100
-5.500 -0.2554 0.05311 0.05081 -0.0515 0.9565 0.0104
-5.250 -0.2195 0.04850 0.04598 -0.0566 0.9171 0.0110
-5.000 -0.1900 0.04523 0.04235 -0.0580 0.8798 0.0115
-4.750 -0.1639 0.04244 0.03922 -0.0583 0.8560 0.0117
-4.500 -0.1399 0.03966 0.03615 -0.0583 0.8381 0.0118
-4.250 -0.1157 0.03689 0.03307 -0.0583 0.8227 0.0119
-4.000 -0.0987 0.03185 0.02784 -0.0591 0.8099 0.0124
-3.750 -0.0762 0.02964 0.02546 -0.0593 0.7982 0.0130
-3.500 -0.0511 0.02757 0.02317 -0.0593 0.7880 0.0140
-3.250 -0.0233 0.02564 0.02098 -0.0590 0.7776 0.0156
-3.000 0.0088 0.02578 0.02076 -0.0578 0.7677 0.0171
-2.750 0.0331 0.02159 0.01621 -0.0579 0.7593 0.0182
-2.500 0.0593 0.01991 0.01440 -0.0581 0.7497 0.0191
-2.250 0.0867 0.01860 0.01291 -0.0580 0.7409 0.0203
-2.000 0.1149 0.01753 0.01161 -0.0577 0.7321 0.0222
-1.750 0.1446 0.01788 0.01175 -0.0572 0.7224 0.0250
-1.500 0.1719 0.01514 0.00874 -0.0572 0.7145 0.0278
-1.250 0.1998 0.01427 0.00779 -0.0572 0.7057 0.0314
-0.250 0.3136 0.01089 0.00396 -0.0558 0.6704 0.0314
0.000 0.3421 0.01059 0.00354 -0.0554 0.6615 0.0258
0.250 0.3700 0.01004 0.00296 -0.0553 0.6520 0.0246
0.500 0.3981 0.00969 0.00255 -0.0552 0.6424 0.0250
0.750 0.4262 0.00938 0.00212 -0.0552 0.6320 0.0275
1.000 0.4545 0.00925 0.00192 -0.0552 0.6204 0.0328
1.250 0.4808 0.00794 0.00186 -0.0557 0.6089 0.5524
1.500 0.5084 0.00682 0.00183 -0.0551 0.5961 1.0000
1.750 0.5358 0.00691 0.00180 -0.0550 0.5804 1.0000
2.000 0.5630 0.00702 0.00179 -0.0549 0.5612 1.0000
2.250 0.5903 0.00715 0.00180 -0.0548 0.5369 1.0000
2.500 0.6173 0.00731 0.00184 -0.0547 0.5097 1.0000
2.750 0.6439 0.00754 0.00190 -0.0546 0.4801 1.0000
3.000 0.6705 0.00779 0.00200 -0.0544 0.4543 1.0000
3.250 0.6972 0.00805 0.00212 -0.0544 0.4353 1.0000
3.500 0.7242 0.00827 0.00228 -0.0543 0.4209 1.0000
3.750 0.7513 0.00848 0.00243 -0.0543 0.4087 1.0000
4.000 0.7785 0.00867 0.00258 -0.0544 0.3983 1.0000
4.250 0.8056 0.00888 0.00275 -0.0544 0.3892 1.0000
4.500 0.8326 0.00909 0.00295 -0.0544 0.3804 1.0000
4.750 0.8599 0.00927 0.00313 -0.0544 0.3721 1.0000
5.000 0.8866 0.00950 0.00333 -0.0544 0.3643 1.0000
5.250 0.9137 0.00967 0.00351 -0.0544 0.3540 1.0000
5.500 0.9406 0.00987 0.00371 -0.0544 0.3420 1.0000
5.750 0.9674 0.01007 0.00391 -0.0544 0.3317 1.0000
6.000 0.9938 0.01031 0.00414 -0.0543 0.3223 1.0000
6.250 1.0208 0.01049 0.00436 -0.0544 0.3126 1.0000
6.500 1.0474 0.01070 0.00461 -0.0543 0.3036 1.0000
6.750 1.0736 0.01094 0.00487 -0.0543 0.2928 1.0000
7.000 1.0998 0.01118 0.00512 -0.0542 0.2798 1.0000
7.250 1.1258 0.01144 0.00540 -0.0541 0.2666 1.0000
7.500 1.1515 0.01173 0.00571 -0.0540 0.2464 1.0000
7.750 1.1754 0.01222 0.00607 -0.0537 0.2146 1.0000
8.000 1.1971 0.01297 0.00661 -0.0531 0.1753 1.0000
8.250 1.2183 0.01377 0.00726 -0.0525 0.1393 1.0000
8.500 1.2347 0.01512 0.00823 -0.0513 0.0797 1.0000
8.750 1.2548 0.01599 0.00903 -0.0505 0.0629 1.0000
9.000 1.2764 0.01664 0.00972 -0.0498 0.0539 1.0000
9.250 1.2975 0.01731 0.01040 -0.0491 0.0446 1.0000
9.500 1.3159 0.01824 0.01124 -0.0481 0.0282 1.0000
9.750 1.3313 0.01945 0.01237 -0.0466 0.0157 1.0000
10.000 1.3467 0.02059 0.01364 -0.0450 0.0129 1.0000
10.250 1.3616 0.02166 0.01484 -0.0434 0.0116 1.0000
10.500 1.3727 0.02296 0.01625 -0.0414 0.0103 1.0000
10.750 1.3722 0.02496 0.01844 -0.0379 0.0093 1.0000
11.000 1.3781 0.02612 0.01972 -0.0351 0.0090 1.0000
11.250 1.3814 0.02759 0.02132 -0.0324 0.0086 1.0000
11.500 1.3829 0.02936 0.02323 -0.0302 0.0083 1.0000
11.750 1.3833 0.03147 0.02548 -0.0284 0.0080 1.0000
12.000 1.3831 0.03388 0.02802 -0.0272 0.0077 1.0000
12.250 1.3825 0.03652 0.03080 -0.0264 0.0074 1.0000
12.500 1.3808 0.03941 0.03384 -0.0259 0.0072 1.0000
12.750 1.3782 0.04252 0.03708 -0.0256 0.0070 1.0000
13.000 1.3743 0.04586 0.04055 -0.0254 0.0069 1.0000
13.250 1.3691 0.04946 0.04427 -0.0254 0.0067 1.0000
13.500 1.3625 0.05327 0.04821 -0.0255 0.0066 1.0000
13.750 1.3542 0.05736 0.05243 -0.0256 0.0064 1.0000
14.000 1.3461 0.06146 0.05668 -0.0258 0.0064 1.0000
14.250 1.3355 0.06597 0.06134 -0.0260 0.0063 1.0000
14.500 1.3247 0.07062 0.06615 -0.0264 0.0062 1.0000
14.750 1.3119 0.07576 0.07147 -0.0270 0.0061 1.0000
15.000 1.2981 0.08134 0.07724 -0.0282 0.0060 1.0000
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Polar data table (+)
Polar graphs
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