GOE 412 AIRFOIL (goe412-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 412 AIRFOIL (goe412-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.73 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe412-il-1000000.txt Download as CSV file: xf-goe412-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 412 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5126 0.03738 0.03507 -0.1206 0.9429 0.0231
-10.750 -0.5220 0.03227 0.02956 -0.1224 0.9312 0.0234
-10.500 -0.5126 0.02995 0.02695 -0.1223 0.9220 0.0237
-10.250 -0.4963 0.02872 0.02548 -0.1219 0.9123 0.0240
-10.000 -0.4852 0.02633 0.02274 -0.1214 0.8994 0.0242
-9.750 -0.4773 0.02273 0.01877 -0.1206 0.8851 0.0246
-9.500 -0.4580 0.02131 0.01717 -0.1201 0.8715 0.0249
-9.250 -0.4362 0.02032 0.01603 -0.1196 0.8589 0.0252
-9.000 -0.4133 0.01949 0.01505 -0.1193 0.8476 0.0255
-8.750 -0.3893 0.01881 0.01425 -0.1190 0.8374 0.0258
-8.500 -0.3646 0.01820 0.01354 -0.1188 0.8288 0.0262
-8.250 -0.3401 0.01749 0.01268 -0.1185 0.8209 0.0266
-8.000 -0.3154 0.01669 0.01173 -0.1183 0.8140 0.0269
-7.750 -0.2902 0.01596 0.01086 -0.1181 0.8073 0.0271
-7.500 -0.2647 0.01532 0.01007 -0.1178 0.8012 0.0274
-7.250 -0.2383 0.01471 0.00936 -0.1177 0.7956 0.0277
-7.000 -0.2119 0.01421 0.00874 -0.1176 0.7899 0.0280
-6.750 -0.1851 0.01379 0.00821 -0.1175 0.7846 0.0283
-6.500 -0.1575 0.01349 0.00784 -0.1175 0.7796 0.0285
-6.250 -0.1314 0.01277 0.00702 -0.1173 0.7744 0.0290
-6.000 -0.1057 0.01203 0.00619 -0.1171 0.7693 0.0293
-5.750 -0.0788 0.01149 0.00561 -0.1170 0.7649 0.0297
-5.500 -0.0516 0.01107 0.00516 -0.1170 0.7600 0.0301
-5.250 -0.0243 0.01074 0.00478 -0.1169 0.7551 0.0304
-5.000 0.0033 0.01044 0.00444 -0.1169 0.7506 0.0308
-4.750 0.0312 0.01015 0.00413 -0.1169 0.7461 0.0313
-4.500 0.0591 0.00990 0.00384 -0.1169 0.7413 0.0318
-4.250 0.0868 0.00971 0.00357 -0.1169 0.7366 0.0323
-4.000 0.1152 0.00949 0.00334 -0.1170 0.7324 0.0329
-3.750 0.1435 0.00931 0.00314 -0.1171 0.7277 0.0335
-3.500 0.1717 0.00917 0.00295 -0.1171 0.7231 0.0339
-3.250 0.1996 0.00894 0.00266 -0.1171 0.7186 0.0348
-3.000 0.2280 0.00874 0.00246 -0.1172 0.7141 0.0359
-2.750 0.2563 0.00859 0.00230 -0.1173 0.7094 0.0371
-2.500 0.2844 0.00851 0.00216 -0.1173 0.7042 0.0385
-2.250 0.3130 0.00839 0.00204 -0.1174 0.6989 0.0401
-2.000 0.3412 0.00824 0.00192 -0.1175 0.6930 0.0479
-1.750 0.3688 0.00808 0.00186 -0.1175 0.6873 0.0798
-1.500 0.3972 0.00796 0.00180 -0.1176 0.6809 0.0956
-1.250 0.4250 0.00790 0.00176 -0.1176 0.6732 0.1130
-1.000 0.4533 0.00784 0.00174 -0.1177 0.6662 0.1295
-0.750 0.4814 0.00779 0.00171 -0.1178 0.6594 0.1444
-0.500 0.5095 0.00775 0.00168 -0.1179 0.6534 0.1595
-0.250 0.5376 0.00766 0.00166 -0.1180 0.6471 0.1824
0.000 0.5648 0.00749 0.00168 -0.1180 0.6410 0.2588
0.250 0.5929 0.00741 0.00170 -0.1181 0.6353 0.3007
0.500 0.6208 0.00734 0.00172 -0.1182 0.6292 0.3365
0.750 0.6480 0.00725 0.00175 -0.1182 0.6232 0.3925
1.000 0.6742 0.00687 0.00182 -0.1181 0.6170 0.5639
1.250 0.6937 0.00617 0.00193 -0.1164 0.6104 0.8448
1.500 0.7367 0.00608 0.00205 -0.1194 0.6034 0.9871
1.750 0.7834 0.00619 0.00210 -0.1237 0.5954 0.9993
2.000 0.8111 0.00627 0.00214 -0.1237 0.5876 1.0000
2.250 0.8364 0.00636 0.00218 -0.1232 0.5792 1.0000
2.500 0.8618 0.00646 0.00224 -0.1227 0.5712 1.0000
2.750 0.8867 0.00657 0.00230 -0.1222 0.5620 1.0000
3.000 0.9119 0.00667 0.00236 -0.1217 0.5523 1.0000
3.250 0.9364 0.00681 0.00244 -0.1210 0.5406 1.0000
3.500 0.9606 0.00698 0.00254 -0.1204 0.5269 1.0000
3.750 0.9848 0.00715 0.00264 -0.1197 0.5122 1.0000
4.000 1.0090 0.00734 0.00276 -0.1190 0.4971 1.0000
4.250 1.0332 0.00753 0.00289 -0.1184 0.4819 1.0000
4.500 1.0569 0.00775 0.00304 -0.1177 0.4654 1.0000
4.750 1.0803 0.00800 0.00320 -0.1169 0.4474 1.0000
5.000 1.1034 0.00826 0.00338 -0.1161 0.4287 1.0000
5.250 1.1260 0.00855 0.00359 -0.1153 0.4093 1.0000
5.500 1.1480 0.00887 0.00381 -0.1143 0.3894 1.0000
5.750 1.1694 0.00921 0.00406 -0.1132 0.3703 1.0000
6.000 1.1910 0.00954 0.00431 -0.1122 0.3521 1.0000
6.250 1.2119 0.00990 0.00458 -0.1111 0.3334 1.0000
6.500 1.2314 0.01031 0.00489 -0.1097 0.3123 1.0000
6.750 1.2498 0.01076 0.00523 -0.1082 0.2914 1.0000
7.000 1.2672 0.01122 0.00557 -0.1064 0.2675 1.0000
7.250 1.2807 0.01176 0.00598 -0.1040 0.2421 1.0000
7.500 1.2932 0.01238 0.00645 -0.1014 0.2158 1.0000
7.750 1.3071 0.01297 0.00694 -0.0992 0.1960 1.0000
8.000 1.3227 0.01351 0.00741 -0.0973 0.1836 1.0000
8.250 1.3392 0.01401 0.00787 -0.0956 0.1754 1.0000
8.500 1.3577 0.01443 0.00830 -0.0943 0.1700 1.0000
8.750 1.3762 0.01485 0.00873 -0.0930 0.1660 1.0000
9.000 1.3930 0.01537 0.00923 -0.0915 0.1606 1.0000
9.250 1.4110 0.01584 0.00971 -0.0903 0.1558 1.0000
9.500 1.4291 0.01630 0.01019 -0.0890 0.1509 1.0000
9.750 1.4449 0.01691 0.01078 -0.0875 0.1453 1.0000
10.000 1.4628 0.01740 0.01130 -0.0863 0.1406 1.0000
10.250 1.4779 0.01807 0.01194 -0.0848 0.1311 1.0000
10.500 1.4841 0.01929 0.01297 -0.0822 0.1005 1.0000
10.750 1.4854 0.02087 0.01441 -0.0792 0.0798 1.0000
11.000 1.4930 0.02211 0.01563 -0.0770 0.0717 1.0000
11.250 1.5038 0.02319 0.01672 -0.0754 0.0646 1.0000
11.500 1.5094 0.02467 0.01814 -0.0733 0.0519 1.0000
11.750 1.5031 0.02707 0.02035 -0.0702 0.0268 1.0000
12.000 1.5068 0.02883 0.02210 -0.0682 0.0205 1.0000
12.250 1.5129 0.03043 0.02373 -0.0665 0.0182 1.0000
12.500 1.5220 0.03182 0.02517 -0.0652 0.0172 1.0000
12.750 1.5300 0.03334 0.02674 -0.0639 0.0163 1.0000
13.000 1.5359 0.03508 0.02853 -0.0625 0.0155 1.0000
13.250 1.5405 0.03697 0.03048 -0.0611 0.0147 1.0000
13.500 1.5487 0.03857 0.03215 -0.0600 0.0143 1.0000
13.750 1.5556 0.04033 0.03397 -0.0590 0.0139 1.0000
14.000 1.5611 0.04227 0.03597 -0.0580 0.0134 1.0000
14.250 1.5654 0.04435 0.03811 -0.0570 0.0131 1.0000
14.500 1.5679 0.04664 0.04046 -0.0559 0.0127 1.0000
14.750 1.5673 0.04933 0.04323 -0.0549 0.0123 1.0000
15.000 1.5636 0.05243 0.04643 -0.0539 0.0120 1.0000
15.250 1.5677 0.05475 0.04882 -0.0533 0.0118 1.0000
15.500 1.5700 0.05728 0.05144 -0.0528 0.0116 1.0000
15.750 1.5713 0.05999 0.05423 -0.0523 0.0114 1.0000
16.000 1.5716 0.06288 0.05719 -0.0519 0.0112 1.0000
16.250 1.5710 0.06593 0.06032 -0.0516 0.0110 1.0000
16.500 1.5693 0.06914 0.06362 -0.0514 0.0108 1.0000
16.750 1.5668 0.07251 0.06707 -0.0513 0.0106 1.0000
17.000 1.5634 0.07604 0.07069 -0.0513 0.0104 1.0000
17.250 1.5588 0.07982 0.07455 -0.0514 0.0103 1.0000
17.500 1.5520 0.08396 0.07877 -0.0517 0.0101 1.0000
17.750 1.5422 0.08855 0.08346 -0.0522 0.0099 1.0000
18.000 1.5298 0.09359 0.08860 -0.0529 0.0098 1.0000
18.250 1.5146 0.09915 0.09428 -0.0538 0.0096 1.0000
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